April 2014 

NASA/TP–2014-218256 

Supersonic Retropropulsion Test 1853 in NASA 

LaRC Unitary Plan Wind Tunnel Test Section 2 

Scott A. Berry and Matthew N. Rhode 

Langley Research Center, Hampton, Virginia 
NASA STI Program . . . in Profile

Since its founding, NASA has been dedicated to the 

advancement of aeronautics and space science. The 

NASA scientific and technical information (STI) 

program plays a key part in helping NASA maintain 

this important role. 

The NASA STI program operates under the 

auspices of the Agency Chief Information Officer. 

It collects, organizes, provides for archiving, and 

disseminates NASA’s STI. The NASA STI 

program provides access to the NASA Aeronautics 

and Space Database and its public interface, the 

NASA Technical Report Server, thus providing one 

of the largest collections of aeronautical and space 

science STI in the world. Results are published in 

both non-NASA channels and by NASA in the 

NASA STI Report Series, which includes the 

following report types: 

• TECHNICAL PUBLICATION. Reports of 

completed research or a major significant phase 

of research that present the results of NASA 

Programs and include extensive data or 

theoretical analysis. Includes compilations of 

significant scientific and technical data and 

information deemed to be of continuing 

reference value. NASA counterpart of peerreviewed formal professional papers, but 

having less stringent limitations on manuscript 

length and extent of graphic presentations. 

• TECHNICAL MEMORANDUM. Scientific 

and technical findings that are preliminary or of 

specialized interest, e.g., quick release reports, 

working papers, and bibliographies that contain 

minimal annotation. Does not contain extensive 

analysis. 

• CONTRACTOR REPORT. Scientific and 

technical findings by NASA-sponsored 

contractors and grantees. 

• CONFERENCE PUBLICATION. 

Collected papers from scientific and 

technical conferences, symposia, seminars, 

or other meetings sponsored or cosponsored by NASA. 

• SPECIAL PUBLICATION. Scientific, 

technical, or historical information from 

NASA programs, projects, and missions, 

often concerned with subjects having 

substantial public interest. 

• TECHNICAL TRANSLATION. 

English-language translations of foreign 

scientific and technical material pertinent to 

NASA’s mission. 

Specialized services also include organizing 

and publishing research results, distributing 

specialized research announcements and feeds, 

providing information desk and personal search 

support, and enabling data exchange services. 

For more information about the NASA STI 

program, see the following: 

• Access the NASA STI program home page 

at http://www.sti.nasa.gov

• E-mail your question to help@sti.nasa.gov

• Fax your question to the NASA STI 

Information Desk at 443-757-5803 

• Phone the NASA STI Information Desk at 

443-757-5802 

• Write to: 

 STI Information Desk 

 NASA Center for AeroSpace Information 

 7115 Standard Drive 

 Hanover, MD 21076-1320
National Aeronautics and 

Space Administration 

Langley Research Center 

Hampton, Virginia 23681-2199 

 

April 2014 

NASA/TP–2014-218256 

Supersonic Retropropulsion Test 1853 in NASA 

LaRC Unitary Plan Wind Tunnel Test Section 2 

Scott A. Berry and Matthew N. Rhode 

Langley Research Center, Hampton, Virginia 
Available from: 

NASA Center for AeroSpace Information 

7115 Standard Drive 

Hanover, MD 21076-1320 

443-757-5802 

Acknowledgments 

The authors would like to acknowledge the support of NASA’s Exploration Technology 

Development and Demonstration (ETDD) Program and Fundamental Aeronautics 

Program (FAP). ETDD’s Entry, Descent, and Landing (EDL) Technology Development 

Project and FAP’s Hypersonics Project, both managed at NASA Langley Research 

Center, jointly supported the work documented herein. The experimental model was 

manufactured at Modern Machine and Tool Company with support from the following 

individuals: Doug Bach, Tim Britt, Ron Dupont, Danny Boulais, Gene Pantaleo, Steve 

Robinette, Jim Rupp, Max Ward, Ken Woodman, Howard Walls, Joe Hudson, Richard 

Vest, Jerry Moore, David Winebarger, David Leatherman, Brian Petritsch, Bill Bent, Tim 

White, Mel Ashley, J.C. Lane, Rex Gay, Brent Meadors, Dennis Yates. The experimental 

test campaign was conducted with the help from the following: Karl Edquist, Chuck 

Player, Chris Laws, Courtney Spells, Andrew McCrea, Bil Kleb, Guy Schauerhamer, 

Kerry Trumble, Bill Oberkampf, Ashley Korzun, Aaron Fuchs, Bryan Falman, Ricky 

Hall, Paul Bagby, and Steve Jones. Posttest analysis support was provided by the 

following: Josh Cordoni (UVA), Juan Cruz (Georgia Tech), Patrick Schultz (UNCC), 

Mike Kegerise, Shann Rufer, and Brett Bathel. Finally, the review committee, consisting 

of Khaled Abdol-Hamid, Bil Kleb, Kelly Murphy, Rob Bauerle, and Diego Capriotti, and 

editorial staff, consisting of Kay Forrest and Staci Altizer, were critical to the completion 

of this report. Thanks for your support!

The use of trademarks or names of manufacturers in this report is for accurate reporting and does not constitute an 

official endorsement, either expressed or implied, of such products or manufacturers by the National Aeronautics 

and Space Administration.
iii

Abstract

A supersonic retropropulsion experiment was conducted in the Langley Research Center Unitary 

Plan Wind Tunnel Test Section 2 at Mach numbers of 2.4, 3.5, and 4.6. Intended as a code 

validation effort, this study used pretest computations to size and refine the model such that 

tunnel blockage and internal flow separations were minimized. A 5-in diameter 70 degree 

sphere-cone forebody, which can accommodate up to four 4:1 area ratio nozzles, followed by a 

9.55 inches long cylindrical aft body was selected for this test after computational maturation. 

The primary measurements for this experiment were high spatial-density surface pressures. In 

addition, high speed schlieren video and internal pressures and temperatures were acquired. The 

test included parametric variations in the number of nozzles utilized, thrust coefficients (roughly 

0 to 4), and angles of attack (–8 to 20 degrees). The run matrix was developed to also allow 

quantification of various sources of experimental uncertainty, such as random errors due to runto-run variations and systematic errors due to flowfield or model misalignments. To 

accommodate the uncertainty assessment, many runs and replicates were conducted with the 

model at various locations within the tunnel and with model roll angles of 0, 60, 120, and 180 

degrees. This test report is intended to provide comprehensive details of the experiment as a 

reference for future computational comparisons and as such contains a review of key 

observations, as well as all schlieren and pressure results within appendices. 
iv

THIS PAGE INTENTIONALLY LEFT BLANK
v

TABLE OF CONTENTS

SECTION 1: INTRODUCTION..................................................................................... 1

SECTION 2: APPARATUS AND METHODS .............................................................. 4

2.1 Facility................................................................................................................ 4

2.2 Model.................................................................................................................. 7

2.3 Instrumentation ............................................................................................... 10

2.4 Test Conditions and Run Matrix..................................................................... 12

2.5 Data Acquisition & Reduction ........................................................................ 13

SECTION 3: TEST SET UP AND EXECUTION......................................................... 15

SECTION 4: DISCUSSION OF RESULTS ................................................................ 19

4.1 Baseline............................................................................................................ 19

4.2 Center Nozzle................................................................................................... 22

4.3 Tri-Nozzle ......................................................................................................... 32

4.4 Quad-nozzle ..................................................................................................... 41

4.5 High Frequency Analysis................................................................................ 48

4.6 Uncertainty Analysis ....................................................................................... 48

SECTION 5: SUMMARY............................................................................................ 50

SECTION 6: REFERENCES...................................................................................... 52

APPENDIX A: MODEL DRAWINGS ......................................................................... 55

APPENDIX B: TEST DETAILS................................................................................ 124

APPENDIX C: SCHLIEREN RESULTS................................................................... 145

APPENDIX D: PRESSURE DATA LINE PLOTS..................................................... 226

APPENDIX E: PRESSURE CONTOUR PLOTS...................................................... 720
vi

LIST OF TABLES

Table 1. Extracted flow features and properties for the center nozzle for  = 0°.30

Table 2. Summary of the pressure coefficient uncertainties at one standard 

deviation.................................................................................................... 49

Table A-1. As-built surface pressure port locations. ............................................... 56

Table A-2. Parameter list and definitions.................................................................. 61

Table B-1. Notional run matrix. ................................................................................ 124

Table B-2. Notational trust coefficients................................................................... 130

Table B-3. Chronological run log............................................................................. 132

Table B-4. Angle of attack sweep schedule............................................................ 142

Table B-5. Statistical analysis of as-tested flow conditions.................................. 143

Table C-1. Schlieren video acquisition information in run chronological order.. 146

Table C-2. Schlieren cases rearranged by configuration. ..................................... 148
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

vii

LIST OF FIGURES

Figure 1. Conceptual sketch of SRP flow features............................................. 2

Figure 2. The Unitary Plan Wind Tunnel complex in Building 1251 at NASA 

Langley Research Center. .................................................................... 4

Figure 3. Schematic of the NASA LaRC Unitary Plan Wind Tunnel complex. . 5

Figure 4. Schematic of the UPWT Test Section 2 nozzle block. ....................... 5

Figure 5. Test Section 2 model support system................................................. 6

Figure 6. Simplified schematic of the UPWT high pressure system. ............... 7

Figure 7. Oblique view of UPWT SRP model assembly. .................................... 8

Figure 8. Major components of UPWT SRP model assembly. .......................... 8

Figure 9. Oblique view of insulator saddle block............................................... 9

Figure 10. Close up of the instrumented center nozzle..................................... 10

Figure 11. Forebody surface instrumentation layout for the baseline 

configuration. ...................................................................................... 11

Figure 12. Test conditions within operating envelope for UPWT Test Section

2........................................................................................................... 13

Figure 13. The SRP model installed in the UPWT Test Section 2. .................... 15

Figure 14. The internal pressure lines and instrumentation wiring.................. 15

Figure 15. The baseline model installed in Test Section 2. ............................... 17

Figure 16. The baseline model installed in the UPWT. ...................................... 17

Figure 17. The center nozzle configuration installed in the UPWT................... 18

Figure 18. The tri-nozzle configuration installed in the UPWT.......................... 18

Figure 19. The effect of Mach number for the baseline configuration at 

 = 0°. ................................................................................................... 20

Figure 20. The effect of angle of attack for the baseline configuration at M∞ =

4.6 (Run 283)........................................................................................ 21

Figure 21. Contour maps showing the effect of angle of attack for the baseline 

configuration at M∞ = 2.4 (Run 274). ................................................. 22

Figure 22. The effect of Mach number for the center nozzle at  = 0° and CT = 

2............................................................................................................ 23

Figure 23. The effect of thrust coefficient for the center nozzle at M∞ = 4.6 and 

 = 0°. ................................................................................................... 24

Figure 24. Comparison of contour maps to Schlieren for a range of thrust 

cases for the center nozzle configuration at M∞ = 2.4 and  = 0° 

(Runs 319, 139, 141, 137, and 136, respectively). ............................. 25

Figure 25. The effect of angle of attack for the center nozzle at M∞ = 4.6 and 

CT = 2 (Run 165)................................................................................... 26

Figure 26. Contour maps showing the effect of angle of attack for the center 

nozzle configuration at M∞ = 2.4 and CT = 2.0, and φ = 0° 

(Run 141).............................................................................................. 27

Figure 27. Relevant dimensions to be extracted from the Schlieren data. ...... 28

Figure 28. Center nozzle shock and plume tracings for all three Mach numbers 

at  = 0°. ............................................................................................... 29
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

viii

Figure 29. Flow feature standoff distance versus nozzle pressure ratio for 

 = 0°. ................................................................................................... 31

Figure 30. Bow shock and plume shapes as a function of  for Mach 4.6, 

CT = 2..................................................................................................... 32

Figure 31. The effect of Mach number for the tri-nozzle at  = 0° and CT = 2. . 33

Figure 32. The effect of thrust coefficient for the tri-nozzle at M∞ = 4.6 and 

 = 0°. ................................................................................................... 34

Figure 33. Comparison of contour maps to schlieren images for a range of 

thrust cases for tri-nozzle configuration at M∞ = 2.4 and  = 0° 

(Runs 180, 221, 202, 198, 194, and 190, respectively). ..................... 35

Figure 34. Comparison of contour maps for complete range of thrust cases for 

tri-nozzle configuration at M∞ = 2.4 and  = 0° (Run 179). .............. 35

Figure 35. The effect of angle of attack for the tri-nozzle at M∞ = 4.6 and CT = 2 

(Run 248).............................................................................................. 36

Figure 36. Comparison of contour maps for a range of angle of attack and roll 

cases for the tri-nozzle configuration at M∞ = 4.6 and CT = 2. ........ 38

Figure 37. Tri nozzle shock and plume tracings for M∞ = 3.5 at  = 0.............. 39

Figure 38. Comparison of center and tri nozzle bow shocks for M∞ = 3.5 at  = 

0............................................................................................................ 40

Figure 39. The effect of Mach number for the quad-nozzle at  = 0° and 

CT = 2.................................................................................................... 41

Figure 40. The effect of thrust coefficient for the quad-nozzle at M∞ = 2.4 and  = 

0°........................................................................................................... 42

Figure 41. The effect of model roll for the quad-nozzle at M∞ = 2.4,  = 0°, and CT = 

3............................................................................................................ 43

Figure 42. The effect of angle of attack for the quad-nozzle at M∞ = 2.4, φ = 0°, 

and CT = 2 (Run 288). .......................................................................... 44

Figure 43. The effect of angle of attack for the quad-nozzle at M∞ = 2.4, φ = 

180°, and CT = 2 (Run 291).................................................................. 45

Figure 44. Comparison of contour maps for a range of angle of attack and roll 

cases for the quad-nozzle configuration at M∞ = 2.4, and CT = 1. .. 47

Figure A-1. View from the front of the model. ...................................................... 55

Figure A-2. View from the port side of the model. ............................................... 56

Figure A-3. SRP model sting showing high pressure air supply port.............. 110

Figure A-4. ULTEM insulator saddle block......................................................... 110

Figure A-5. Manifold assembly. ........................................................................... 111

Figure A-6. Initial assembly of forebody and manifold...................................... 111

Figure A-7. Forebody assembly with baseline inserts installed....................... 112

Figure A-8. Six of eight baseline and nozzle inserts. ........................................ 112

Figure A-9. Instrumented half aft shell................................................................ 113

Figure A-10. Rear cover support plate showing wiring access hole.................. 113

Figure A-11. Assembly of sting and rear cover support plate............................ 114
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

ix

Figure A-12. Backside of forebody showing pressure tube port posts and shims 

for inserts........................................................................................... 114

Figure A-13. Sting assembly with Kulite pressure transducers installed.......... 115

Figure A-14. Insulator saddle block with one ESP module attached. ................ 115

Figure A-15. Installation of the double O-rings for each insert. ......................... 116

Figure A-16. Center plug installation prior to seating the insert past the 

O-rings. .............................................................................................. 116

Figure A-17. All four baseline plug inserts in the proper (seated) position....... 117

Figure A-18. Forebody guide posts used for proper alignment of manifold during 

assembly............................................................................................ 117

Figure A-19. Installation of bolts that hold forebody in place............................. 118

Figure A-20. O-ring between manifold and sting/plenum.................................... 118

Figure A-21. Installation of bolts that hold manifold to sting. ............................ 119

Figure A-22. Installation of saddle block with one ESP module attached. ........ 119

Figure A-23. Close-up of a saddle block thermocouple for monitoring ESP 

module temperatures........................................................................ 120

Figure A-24. Installation of the aft cover plates. .................................................. 120

Figure A-25. View showing model internal volume before installation of pressure 

tubes. ................................................................................................. 121

Figure A-26. Close-up showing clearance between ESP module and aft cover 

plate.................................................................................................... 121

Figure A-27. Installation of second aft cover plate. ............................................. 122

Figure A-28. Fully assembled model with baseline inserts................................. 122

Figure A-29. All four nozzle inserts in the proper (seated) position................... 123

Figure A-30. Assembly of the forebody and manifold with nozzle inserts. ....... 123

Figure C-1. Run 58: baseline schlieren video images for range of  at M∞ =

3.5, CT = 0.0, and φ = 60 deg............................................................. 151

Figure C-2. Run 67: baseline Schlieren video images for range of  = at M∞ =

3.5, CT = 0.0, and φ = 60 deg............................................................. 152

Figure C-3. Run 86: baseline Schlieren video images for range of  = at 

M∞ = 4.6, CT = 0.0, and φ = 0 deg..................................................... 154

Figure C-4. Run 106: baseline Schlieren video images for range of  at M∞ =

4.6, CT = 0.0, and φ = 120 deg........................................................... 156

Figure C-5. Run 136: center nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 4.0, and φ= 0 deg. .................................................... 158

Figure C-6. Run 137: center nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 3.0, and φ = 0 deg..................................................... 159

Figure C-7. Run 139: center nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 1.0, and φ= 180 deg. ................................................ 160

Figure C-8. Run 141: center nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 2.0, and φ = 180 deg................................................. 161

Figure C-9. Run 150: center nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 3.0, and φ = 0 deg..................................................... 162
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

x

Figure C-10. Run 153: center nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 2.0, and φ = 0 deg..................................................... 163

Figure C-11. Run 154: center nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 1.0, and φ= 0 deg. .................................................... 164

Figure C-12. Run 157: center nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 0.5, and φ= 0 deg. .................................................... 165

Figure C-13. Run 158: center nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 0.2, and φ= 0 deg. .................................................... 166

Figure C-14. Run 163: center nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 3.0, and φ= 0 deg. .................................................... 167

Figure C- 15. Run 165: center nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 2.0, and φ =deg...................................................... 168

Figure C-16. Run 167: center nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 1.0, and φ = 0 deg..................................................... 169

Figure C-17. Run 169: center nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 0.5, and φ = 180 deg................................................. 170

Figure C-18. Run 171: center nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 0.2, and φ =180 deg. ................................................. 171

Figure C-19. Run 180: tri-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 0.0, and φ = deg...................................................... 171

Figure C-20. Run 185: tri-nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 0.0, and φ= deg. ....................................................... 172

Figure C-21. Run 190: tri-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 3.0, and φ = 0 deg..................................................... 174

Figure C-22. Run 192: tri-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 3.0, and φ= 120deg.................................................. 175

Figure C-23. Run 194: tri-nozzle schlieren video images for range of  at M∞ =

2.4, CT = 2.0, and φ = 180 deg........................................................... 175

Figure C-24. Run 198: tri-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 1.0, and φ = 0 deg..................................................... 176

Figure C-25. Run 202: tri-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 0.43, and φ = 180 deg............................................... 177

Figure C-26. Run 206: tri-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 0.43, and φ = 0 deg................................................... 178

Figure C-27. Run 212: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 2.93, and φ = 60 deg................................................. 179

Figure C-28. Run 214: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 2.95, and φ = 180 deg. .............................................. 180

Figure C-29. Run 221: tri-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 0.24, and φ = 0 deg................................................... 182

Figure C-30. Run 222: tri-nozzle schlieren video images for range of  at M∞ =

3.5, CT = 2.96, and φ = 0 deg............................................................. 182
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xi

Figure C-31. Run 225: tri-nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 2.99, and φ = 180 deg............................................... 184

Figure C-32. Run 226: tri-nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 1.96, and φ= 180 deg. .............................................. 185

Figure C-33. Run 247: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 1.92, and φ= 0 deg. .................................................. 186

Figure C-34. Run 248: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 1.93, and φ = 180 deg............................................... 188

Figure C-35. Run 249: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 0.90, and φ= 180 deg. .............................................. 189

Figure C-36. Run 253: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 0.43, and φ = 0 deg................................................... 190

Figure C-37. Run 257: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 0.20, and φ = 0 deg................................................... 191

Figure C-38. Run 262: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 2.94, and φ = 0 deg................................................... 192

Figure C-39. Run 263: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 2.94, and φ = 180deg. .............................................. 193

Figure C-40. Run 264: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6,  = 0 deg, and φ = 60 deg. ............................................... 194

Figure C-41. Run 264: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6,  = 12 deg, and φ = 60 deg. ............................................. 195

Figure C-42. Run 265: tri-nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 0.91, and φ= 0 deg. .................................................. 195

Figure C-43. Run 266: tri-nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 0.83, and φ = 0 deg................................................... 196

Figure C-44. Run 267: tri-nozzle schlieren video images for range of  at 

M∞ = 3.5 and  = 0 deg. .................................................................... 197

Figure C-45. Run 274: baseline schlieren video images for range of  at 

M∞ = 2.4, CT = 0.0, and φ = 180 deg................................................. 200

Figure C-46. Run 276: baseline schlieren video images for range of  at 

M∞ = 3.5, CT = 0.0, and φ= 180 deg. ................................................ 202

Figure C-47. Run 283: baseline schlieren video images for range of  at 

M∞ = 4.6, CT = 0.0, and φ = 180 deg................................................. 204

Figure C-48. Run 288: quad-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 1.93, and φ = 0 deg................................................... 206

Figure C-49. Run 291: quad-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 1.94, and φ = 180 deg............................................... 208

Figure C-50. Run 292: quad-nozzle schlieren video images for range of model 

positions at M∞ = 2.4,  = 0 deg, and CT = 1.93. ............................ 209

Figure C-51. Run 293: quad-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 0.94, and φ = 180 deg............................................... 210
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xii

Figure C-52. Run 297: quad-nozzle schlieren video images for range of model 

positions at M∞ = 2.4,  = 0 deg, and CT = 2.95. ............................ 211

Figure C-53. Run 298: quad-nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 1.91, and φ = 0 deg................................................... 212

Figure C-54. Run 301: quad-nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 1.92, and φ = 180 deg............................................... 213

Figure C-55. Run 305: quad-nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 0.90, and φ = 0 deg................................................... 214

Figure C-56. Run 306: quad-nozzle schlieren video images for range of model 

positions at M∞ = 3.5 and  = 0 deg. .............................................. 215

Figure C-57. Run 307: quad-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 1.92, and φ = 0 deg................................................... 216

Figure C-58. Run 311: quad-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 1.93, and φ = 180 deg............................................... 217

Figure C-59. Run 315: quad-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 0.91, and φ = 0 deg................................................... 218

Figure C-60. Run 318: center nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 1.98, and φ = 0 deg................................................... 219

Figure C-61. Run 319: center nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 0.46, and φ = 0 deg................................................... 221

Figure C-62. Run 320: center nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 1.96, and φ = 0 deg................................................... 222

Figure C-63. Run 321: center nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 1.96, and φ = 0 deg................................................... 223

Figure D-1. Baseline configuration, Run 013, M∞ = 2.4, Re∞ = 1.0x106/ft, φ

= 0.03°, XS = 25.16 in, YS = 0.03 in, CT = 0.00. .................................. 227

Figure D-2. Baseline configuration, Run 014, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.97°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.............................. 229

Figure D-3. Baseline configuration, Run 016, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 25.16 in, YS = 0.00 in, CT = 0.00................................ 231

Figure D-4. Baseline configuration, Run 017, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 59.86°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.............................. 233

Figure D-5. Baseline configuration, Run 018, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.96°, XS = 25.16 in, YS = 0.00 in, CT = 0.00............................ 235

Figure D-6. Baseline configuration, Run 019, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.91°, XS = 25.16 in, YS = 0.00 in, CT = 0.00............................ 237

Figure D-7. Baseline configuration, Run 020, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 39.93 in, YS = 0.00 in, CT = 0.00................................ 239

Figure D-8. Baseline configuration, Run 021, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 59.88°, XS = 39.93 in, YS = 0.00 in, CT = 0.00.............................. 241

Figure D-9. Baseline configuration, Run 022, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 120.06°, XS = 39.93 in, YS = 0.00 in, CT = 0.00............................ 243
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xiii

Figure D-10. Baseline configuration, Run 023, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 39.93 in, YS = 0.00 in, CT = 0.00............................ 245

Figure D-11. Baseline configuration, Run 024, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 39.93 in, YS = 0.00 in, CT = 0.00................................ 247

Figure D-12. Baseline configuration, Run 025, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.08°, XS = 39.93 in, YS = 0.00 in, CT = 0.00.............................. 249

Figure D-13. Baseline configuration, Run 026, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.03°, XS = 50.17 in, YS = 0.00 in, CT = 0.00................................ 251

Figure D-14. Baseline configuration, Run 027, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.08°, XS = 50.17 in, YS = 0.00 in, CT = 0.00.............................. 253

Figure D-15. Baseline configuration, Run 028, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 120.06°, XS = 50.17 in, YS = 0.00 in, CT = 0.00............................ 255

Figure D-16. Baseline configuration, Run 029, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.91°, XS = 50.17 in, YS = 0.00 in, CT = 0.00............................ 257

Figure D-17. Baseline configuration, Run 030, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.91°, XS = 25.18 in, YS = 0.00 in, CT = 0.00............................ 259

Figure D-18. Baseline configuration, Run 031, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.92°, XS = 25.18 in, YS = 0.00 in, CT = 0.00............................ 261

Figure D-19. Baseline configuration, Run 032, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 25.18 in, YS = 0.00 in, CT = 0.00.............................. 263

Figure D-20. Baseline configuration, Run 033, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 25.18 in, YS = 0.00 in, CT = 0.00................................ 265

Figure D-21. Baseline configuration, Run 034, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 25.18 in, YS = 7.99 in, CT = 0.00................................ 267

Figure D-22. Baseline configuration, Run 035, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.08°, XS = 25.18 in, YS = 7.99 in, CT = 0.00.............................. 269

Figure D-23. Baseline configuration, Run 036, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.90°, XS = 25.18 in, YS = 7.99 in, CT = 0.00............................ 271

Figure D-24. Baseline configuration, Run 037, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 25.18 in, YS = 7.99 in, CT = 0.00............................ 273

Figure D-25. Baseline configuration, Run 038, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.19 in, YS = 7.99 in, CT = 0.00............................ 275

Figure D-26. Baseline configuration, Run 039, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.90°, XS = 40.19 in, YS = 7.99 in, CT = 0.00............................ 277

Figure D-27. Baseline configuration, Run 040, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.92°, XS = 40.19 in, YS = 7.99 in, CT = 0.00.............................. 279

Figure D-28. Baseline configuration, Run 041, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 40.19 in, YS = 7.99 in, CT = 0.00................................ 281

Figure D-29. Baseline configuration, Run 042, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.19 in, YS = −8.00 in, CT = 0.00. .......................... 283

Figure D-30. Baseline configuration, Run 043, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.92°, XS = 40.19 in, YS = −8.00 in, CT = 0.00. .......................... 285

Figure D-31. Baseline configuration, Run 044, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.90°, XS = 40.19 in, YS = –8.00 in, CT = 0.00.......................... 287
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xiv

Figure D-32. Baseline configuration, Run 045, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.19 in, YS = –8.00 in, CT = 0.00.......................... 289

Figure D-33. Baseline configuration, Run 046, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 50.16 in, YS = –8.00 in, CT = 0.00.......................... 291

Figure D-34. Baseline configuration, Run 047, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.98°, XS = 50.16 in, YS = –8.00 in, CT = 0.00.......................... 293

Figure D-35. Baseline configuration, Run 048, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 50.16 in, YS = –8.00 in, CT = 0.00............................ 295

Figure D-36. Baseline configuration, Run 049, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 50.16 in, YS = –8.00 in, CT = 0.00.............................. 297

Figure D-37. Baseline configuration, Run 050, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.96°, XS = 50.16 in, YS = 0.00 in, CT = 0.00.............................. 299

Figure D-38. Baseline configuration, Run 051, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.94°, XS = 50.16 in, YS = 0.00 in, CT = 0.00............................ 301

Figure D-39. Baseline configuration, Run 052, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 50.16 in, YS = 0.00 in, CT = 0.00............................ 303

Figure D-40. Baseline configuration, Run 053, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 39.93 in, YS = 0.00 in, CT = 0.00................................ 305

Figure D-41. Baseline configuration, Run 054, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.06°, XS = 40.17 in, YS = 0.00 in, CT = 0.00............................ 307

Figure D-42. Baseline configuration, Run 055, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.17 in, YS = 0.00 in, CT = 0.00.............................. 309

Figure D-43. Baseline configuration, Run 056, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.07°, XS = 40.17 in, YS = 0.00 in, CT = 0.00. ............................ 311

Figure D-44. Baseline configuration, Run 057, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.07°, XS = 25.16 in, YS = 0.00 in, CT = 0.00. ............................ 313

Figure D-45. Baseline configuration, Run 058, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.98°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.............................. 315

Figure D-46. Baseline configuration, Run 059, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 120.12°, XS = 25.16 in, YS = 0.00 in, CT = 0.00............................ 317

Figure D-47. Baseline configuration, Run 060, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 25.16 in, YS = 0.00 in, CT = 0.00............................ 319

Figure D-48. Baseline configuration, Run 065, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.01°, XS = 25.16 in, YS = −8.00 in, CT = 0.00. .......................... 321

Figure D-49. Baseline configuration, Run 067, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 60.00°, XS = 25.16 in, YS = –8.00 in, CT = 0.00............................ 323

Figure D-50. Baseline configuration, Run 068, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.02°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.......................... 325

Figure D-51. Baseline configuration, Run 069, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 179.95°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.......................... 327

Figure D-52. Baseline configuration, Run 070, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.16 in, YS = –8.00 in, CT = 0.00.......................... 329

Figure D-53. Baseline configuration, Run 073, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.98°, XS = 40.18 in, YS = –8.00 in, CT = 0.00.......................... 331
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xv

Figure D-54. Baseline configuration, Run 074, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.96°, XS = 40.18 in, YS = –8.00 in, CT = 0.00............................ 333

Figure D-55. Baseline configuration, Run 075, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.03°, XS = 40.18 in, YS = –8.00 in, CT = 0.00.............................. 335

Figure D-56. Baseline configuration, Run 076, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 0.03°, XS = 40.18 in, YS = 7.99 in, CT = 0.00................................ 337

Figure D-57. Baseline configuration, Run 077, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.93°, XS = 40.16 in, YS = 7.99 in, CT = 0.00.............................. 339

Figure D-58. Baseline configuration, Run 078, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.98°, XS = 40.16 in, YS = 7.95 in, CT = 0.00............................ 341

Figure D-59. Baseline configuration, Run 079, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −179.99°, XS = 40.16 in, YS = 7.95 in, CT = 0.00. ........................ 343

Figure D-60. Baseline configuration, Run 080, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −179.99°, XS = 50.15 in, YS = 7.95 in, CT = 0.00. ........................ 345

Figure D-61. Baseline configuration, Run 081, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 119.98°, XS = 50.15 in, YS = 7.95 in, CT = 0.00............................ 347

Figure D-62. Baseline configuration, Run 082, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.94°, XS = 50.15 in, YS = 7.95 in, CT = 0.00.............................. 349

Figure D-63. Baseline configuration, Run 083, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 0.01°, XS = 50.15 in, YS = 7.95 in, CT = 0.00................................ 351

Figure D-64. Baseline configuration, Run 086, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 0.01°, XS = 25.17 in, YS = 0.00 in, CT = 0.00................................ 353

Figure D-65. Baseline configuration, Run 087, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 59.98°, XS = 25.17 in, YS = 0.00 in, CT = 0.00.............................. 355

Figure D-66. Baseline configuration, Run 088, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 119.96°, XS = 25.17 in, YS = 0.00 in, CT = 0.00............................ 357

Figure D-67. Baseline configuration, Run 089, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 179.91°, XS = 25.17 in, YS = 0.00 in, CT = 0.00............................ 359

Figure D-68. Baseline configuration, Run 090, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.00................................ 361

Figure D-69. Baseline configuration, Run 091, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 59.94°, XS = 40.18 in, YS = 0.00 in, CT = 0.00.............................. 363

Figure D-70. Baseline configuration, Run 092, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 119.98°, XS = 40.18 in, YS = 0.00 in, CT = 0.00............................ 365

Figure D-71. Baseline configuration, Run 093, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 179.91°, XS = 40.18 in, YS = 0.00 in, CT = 0.00............................ 367

Figure D-72. Baseline configuration, Run 094, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 179.91°, XS = 50.14 in, YS = 0.00 in, CT = 0.00............................ 369

Figure D-73. Baseline configuration, Run 095, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 119.96°, XS = 50.14 in, YS = 0.00 in, CT = 0.00............................ 371

Figure D-74. Baseline configuration, Run 096, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 59.90°, XS = 50.14 in, YS = 0.00 in, CT = 0.00.............................. 373

Figure D-75. Baseline configuration, Run 097, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = −0.07°, XS = 50.14 in, YS = 0.00 in, CT = 0.00. ............................ 375
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xvi

Figure D-76. Baseline configuration, Run 098, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = −0.07°, XS = 50.14 in, YS = 7.99 in, CT = 0.00. ............................ 377

Figure D-77. Baseline configuration, Run 099, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 59.86°, XS = 50.14 in, YS = 7.99 in, CT = 0.00.............................. 379

Figure D-78. Baseline configuration, Run 100, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 120.06°, XS = 50.14 in, YS = 7.99 in, CT = 0.00............................ 381

Figure D-79. Baseline configuration, Run 101, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 179.97°, XS = 50.14 in, YS = 7.99 in, CT = 0.00............................ 383

Figure D-80. Baseline configuration, Run 104, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.03°, XS = 25.19 in, YS = 0.00 in, CT = 0.00. ............................ 384

Figure D-81. Baseline configuration, Run 105, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.94°, XS = 25.19 in, YS = 0.00 in, CT = 0.00.............................. 386

Figure D-82. Baseline configuration, Run 106, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.02°, XS = 25.19 in, YS = 0.00 in, CT = 0.00............................ 388

Figure D-83. Baseline configuration, Run 107, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.93°, XS = 25.19 in, YS = 0.00 in, CT = 0.00............................ 390

Figure D-84. Baseline configuration, Run 108, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.93°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 392

Figure D-85. Baseline configuration, Run 109, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 119.98°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 394

Figure D-86. Baseline configuration, Run 110, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.88°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.............................. 396

Figure D-87. Baseline configuration, Run 111, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.01°, XS = 40.09 in, YS = 0.00 in, CT = 0.00. ............................ 398

Figure D-88. Baseline configuration, Run 112, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.01°, XS = 50.19 in, YS = 0.00 in, CT = 0.00. ............................ 400

Figure D-89. Baseline configuration, Run 113, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.96°, XS = 50.19 in, YS = 0.00 in, CT = 0.00.............................. 402

Figure D-90. Baseline configuration, Run 114, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.10°, XS = 50.19 in, YS = 0.00 in, CT = 0.00............................ 404

Figure D-91. Baseline configuration, Run 115, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.97°, XS = 50.19 in, YS = 0.00 in, CT = 0.00............................ 406

Figure D-92. Baseline configuration, Run 116, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.97°, XS = 50.19 in, YS = 8.00 in, CT = 0.00............................ 408

Figure D- 93. Baseline configuration, Run 117, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 119.98°, XS = 50.19 in, YS = 8.00 in, CT = 0.00............................ 410

Figure D-94. Baseline configuration, Run 118, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.90°, XS = 50.19 in, YS = 8.00 in, CT = 0.00.............................. 412

Figure D-95. Baseline configuration, Run 119, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.03°, XS = 50.19 in, YS = 8.00 in, CT = 0.00................................ 414

Figure D-96. Baseline configuration, Run 120, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.03°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.............................. 416

Figure D-97. Baseline configuration, Run 121, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 60.00°, XS = 25.16 in, YS = –8.00 in, CT = 0.00............................ 418
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xvii

Figure D-98. Baseline configuration, Run 122, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.06°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.......................... 420

Figure D-99. Baseline configuration, Run 123, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.93°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.......................... 422

Figure D-100. Center nozzle configuration, Run 136, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.01°, XS = 40.16 in, YS = 0.00 in, CT = 3.96. ............................ 424

Figure D-101. Center nozzle configuration, Run 137, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 3.01. ............................ 426

Figure D-102. Center nozzle configuration, Run 138, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 3.02............................ 428

Figure D-103. Center nozzle configuration, Run 139, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 0.97............................ 430

Figure D-104. Center nozzle configuration, Run 140, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.97. ............................ 432

Figure D-105. Center nozzle configuration, Run 141, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 1.98. ............................ 434

Figure D-106. Center nozzle configuration, Run 142, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.91°, XS = 40.15 in, YS = 0.00 in, CT = 1.97. ........................ 436

Figure D-107. Center nozzle configuration, Run 143, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.91°, XS = 40.15 in, YS = 0.00 in, CT = 0.47. ........................ 438

Figure D-108. Center nozzle configuration, Run 144, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.46................................ 440

Figure D-109. Center nozzle configuration, Run 145, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.23................................ 442

Figure D-110. Center nozzle configuration, Run 146, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.23............................ 444

Figure D-111. Center nozzle configuration, Run 148, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 446

Figure D-112. Center nozzle configuration, Run 149, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.00. ............................ 448

Figure D-113. Center nozzle configuration, Run 150, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.03°, XS = 40.17 in, YS = 0.00 in, CT = 2.99. ............................ 450

Figure D-114. Center nozzle configuration, Run 151, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −179.97°, XS = 40.17 in, YS = 0.00 in, CT = 2.98. ........................ 452

Figure D-115. Center nozzle configuration, Run 152, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −179.97°, XS = 40.17 in, YS = 0.00 in, CT = 1.97. ........................ 454

Figure D-116. Center nozzle configuration, Run 153, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.09°, XS = 40.17 in, YS = 0.00 in, CT = 1.96. ............................ 456

Figure D-117. Center nozzle configuration, Run 154, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.09°, XS = 40.17 in, YS = 0.00 in, CT = 0.92. ............................ 458

Figure D-118. Center nozzle configuration, Run 155, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 179.91°, XS = 40.17 in, YS = 0.00 in, CT = 0.94............................ 460

Figure D-119. Center nozzle configuration, Run 156, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 179.93°, XS = 40.17 in, YS = 0.00 in, CT = 0.46............................ 462
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xviii

Figure D-120. Center nozzle configuration, Run 157, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.07°, XS = 40.17 in, YS = 0.00 in, CT = 0.45................................ 464

Figure D-121. Center nozzle configuration, Run 159, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.01°, XS = 40.17 in, YS = 0.00 in, CT = 0.21. ............................ 466

Figure D-122. Center nozzle configuration, Run 160, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.93°, XS = 40.17 in, YS = 0.00 in, CT = 0.21............................ 468

Figure D-123. Center nozzle configuration, Run 161, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.93°, XS = 40.17 in, YS = 0.00 in, CT = 0.00............................ 470

Figure D-124. Center nozzle configuration, Run 162, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.03°, XS = 40.17 in, YS = 0.00 in, CT = 0.00................................ 472

Figure D-125. Center nozzle configuration, Run 163, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.03°, XS = 40.17 in, YS = 0.00 in, CT = 2.97................................ 474

Figure D-126. Center nozzle configuration, Run 164, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.93°, XS = 40.17 in, YS = 0.00 in, CT = 2.95............................ 476

Figure D-127. Center nozzle configuration, Run 165, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.93°, XS = 40.15 in, YS = 0.00 in, CT = 1.98............................ 478

Figure D-128. Center nozzle configuration, Run 166, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.03°, XS = 40.15 in, YS = 0.00 in, CT = 1.97................................ 480

Figure D-129. Center nozzle configuration, Run 167, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.96................................ 482

Figure D-130. Center nozzle configuration, Run 168, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.93............................ 484

Figure D-131. Center nozzle configuration, Run 169, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.46............................ 486

Figure D-132. Center nozzle configuration, Run 170, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.46................................ 488

Figure D-133. Center nozzle configuration, Run 171, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.22................................ 490

Figure D-134. Center nozzle configuration, Run 172, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.91°, XS = 40.15 in, YS = 0.00 in, CT = 0.22............................ 492

Figure D-135. Center nozzle configuration, Run 173, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.91°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 494

Figure D-136. Center nozzle configuration, Run 174, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.07°, XS = 40.15 in, YS = 0.00 in, CT = 0.00. ............................ 496

Figure D-137. Tri-nozzle configuration, Run 180, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.00. ............................ 498

Figure D-138. Tri-nozzle configuration, Run 181, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 500

Figure D-139. Tri-nozzle configuration, Run 182, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 120.02°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 502

Figure D-140. Tri-nozzle configuration, Run 183, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.............................. 504

Figure D-141. Tri-nozzle configuration, Run 184, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.00................................ 506
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xix

Figure D-142. Tri-nozzle configuration, Run 185, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.88°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.............................. 508

Figure D-143. Tri-nozzle configuration, Run 186, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 120.00°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 510

Figure D-144. Tri-nozzle configuration, Run 187, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 512

Figure D-145. Tri-nozzle configuration, Run 190, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 2.94. ............................ 514

Figure D-146. Tri-nozzle configuration, Run 191, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.88°, XS = 40.15 in, YS = 0.00 in, CT = 2.92.............................. 516

Figure D-147. Tri-nozzle configuration, Run 192, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 120.00°, XS = 40.15 in, YS = 0.00 in, CT = 2.94............................ 518

Figure D-148. Tri-nozzle configuration, Run 193, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.97°, XS = 40.15 in, YS = 0.00 in, CT = 2.96. ........................ 520

Figure D-149. Tri-nozzle configuration, Run 194, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −179.97°, XS = 40.15 in, YS = 0.00 in, CT = 1.94. ........................ 522

Figure D-150. Tri-nozzle configuration, Run 195, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 120.02°, XS = 40.15 in, YS = 0.00 in, CT = 1.93............................ 524

Figure D-151. Tri-nozzle configuration, Run 196, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.88°, XS = 40.15 in, YS = 0.00 in, CT = 1.93.............................. 526

Figure D-152. Tri-nozzle configuration, Run 197, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 1.94. ............................ 528

Figure D-153. Tri-nozzle configuration, Run 198, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.94. ............................ 530

Figure D-154. Tri-nozzle configuration, Run 199, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.92°, XS = 40.15 in, YS = 0.00 in, CT = 0.94.............................. 532

Figure D-155. Tri-nozzle configuration, Run 200, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 120.00°, XS = 40.15 in, YS = 0.00 in, CT = 0.94............................ 534

Figure D-156. Tri-nozzle configuration, Run 201, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.94............................ 536

Figure D-157. Tri-nozzle configuration, Run 202, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.43............................ 538

Figure D-158. Tri-nozzle configuration, Run 203, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −179.97°, XS = 40.15 in, YS = 0.00 in, CT = 0.44. ........................ 540

Figure D-159. Tri-nozzle configuration, Run 204, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 120.04°, XS = 40.15 in, YS = 0.00 in, CT = 0.43............................ 542

Figure D-160. Tri-nozzle configuration, Run 205, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.88°, XS = 40.15 in, YS = 0.00 in, CT = 0.44.............................. 544

Figure D-161. Tri-nozzle configuration, Run 206, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.43. ............................ 546

Figure D-162. Tri-nozzle configuration, Run 211, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 2.93. ............................ 548

Figure D-163. Tri-nozzle configuration, Run 212, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.96°, XS = 40.15 in, YS = 0.00 in, CT = 2.94.............................. 550
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xx

Figure D-164. Tri-nozzle configuration, Run 213, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.04°, XS = 40.15 in, YS = 0.00 in, CT = 2.87............................ 552

Figure D-165. Tri-nozzle configuration, Run 214, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 2.96............................ 554

Figure D-166. Tri-nozzle configuration, Run 217, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.47. ............................ 556

Figure D-167. Tri-nozzle configuration, Run 218, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.88°, XS = 40.15 in, YS = 0.00 in, CT = 0.48.............................. 558

Figure D-168. Tri-nozzle configuration, Run 219, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 120.02°, XS = 40.15 in, YS = 0.00 in, CT = 0.47............................ 560

Figure D-169. Tri-nozzle configuration, Run 220, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.48............................ 562

Figure D-170. Tri-nozzle configuration, Run 221, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.24. ............................ 564

Figure D-171. Tri-nozzle configuration, Run 222, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 2.94. ............................ 566

Figure D-172. Tri-nozzle configuration, Run 223, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.90°, XS = 40.15 in, YS = 0.00 in, CT = 2.95.............................. 568

Figure D-173. Tri-nozzle configuration, Run 224, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 120.06°, XS = 40.15 in, YS = 0.00 in, CT = 2.97............................ 570

Figure D-174. Tri-nozzle configuration, Run 225, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 2.97............................ 572

Figure D-175. Tri-nozzle configuration, Run 226, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 1.96............................ 574

Figure D-176. Tri-nozzle configuration, Run 227, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.04°, XS = 40.15 in, YS = 0.00 in, CT = 1.95............................ 576

Figure D-177. Tri-nozzle configuration, Run 228, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.96°, XS = 40.15 in, YS = 0.00 in, CT = 1.94.............................. 578

Figure D-178. Tri-nozzle configuration, Run 229, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 1.94. ............................ 580

Figure D-179. Tri-nozzle configuration, Run 230, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.96. ............................ 582

Figure D-180. Tri-nozzle configuration, Run 233, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 59.90°, XS = 40.15 in, YS = 0.00 in, CT = 0.97.............................. 584

Figure D-181. Tri-nozzle configuration, Run 234, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.96. ............................ 586

Figure D-182. Tri-nozzle configuration, Run 235, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 120.06°, XS = 40.15 in, YS = 0.00 in, CT = 0.96............................ 588

Figure D-183. Tri-nozzle configuration, Run 236, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.97............................ 590

Figure D-184. Tri-nozzle configuration, Run 237, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.48............................ 592

Figure D-185. Tri-nozzle configuration, Run 238, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.00°, XS = 40.15 in, YS = 0.00 in, CT = 0.47............................ 594
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xxi

Figure D-186. Tri-nozzle configuration, Run 239, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.46.............................. 596

Figure D-187. Tri-nozzle configuration, Run 240, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.46. ............................ 598

Figure D-188. Tri-nozzle configuration, Run 241, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.23. ............................ 600

Figure D-189. Tri-nozzle configuration, Run 242, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 1.96. ............................ 602

Figure D-190. Tri-nozzle configuration, Run 243, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.94°, XS = 40.15 in, YS = 0.00 in, CT = 1.96.............................. 604

Figure D-191. Tri-nozzle configuration, Run 244, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.06°, XS = 40.15 in, YS = 0.00 in, CT = 1.96............................ 606

Figure D-192. Tri-nozzle configuration, Run 245, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −179.99°, XS = 40.15 in, YS = 0.00 in, CT = 1.96. ........................ 608

Figure D-193. Tri-nozzle configuration, Run 247, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 1.92. ............................ 610

Figure D-194. Tri-nozzle configuration, Run 248, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 1.93............................ 612

Figure D-195. Tri-nozzle configuration, Run 249, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.90............................ 614

Figure D-196. Tri-nozzle configuration, Run 250, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.04°, XS = 40.15 in, YS = 0.00 in, CT = 0.90............................ 616

Figure D-197. Tri-nozzle configuration, Run 251, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.98°, XS = 40.15 in, YS = 0.00 in, CT = 0.89.............................. 618

Figure D-198. Tri-nozzle configuration, Run 252, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.90. ............................ 620

Figure D-199. Tri-nozzle configuration, Run 253, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.43. ............................ 622

Figure D-200. Tri-nozzle configuration, Run 254, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.43.............................. 624

Figure D-201. Tri-nozzle configuration, Run 255, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.02°, XS = 40.15 in, YS = 0.00 in, CT = 0.42............................ 626

Figure D-202. Tri-nozzle configuration, Run 256, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.43............................ 628

Figure D-203. Tri-nozzle configuration, Run 257, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.20. ............................ 630

Figure D-204. Tri-nozzle configuration, Run 258, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.00. ............................ 632

Figure D-205. Tri-nozzle configuration, Run 259, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.90°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.............................. 634

Figure D-206. Tri-nozzle configuration, Run 260, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.00°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 636

Figure D-207. Tri-nozzle configuration, Run 261, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 638
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xxii

Figure D-208. Tri-nozzle configuration, Run 262, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.01°, XS = 40.15 in, YS = 0.00 in, CT = 2.92................................ 640

Figure D-209. Tri-nozzle configuration, Run 263, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −179.95°, XS = 40.15 in, YS = 0.00 in, CT = 2.94. ........................ 642

Figure D-210. Tri-nozzle configuration, Run 265, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.91. ............................ 644

Figure D-211. Tri-nozzle configuration, Run 266, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.44. ............................ 646

Figure D-212. Baseline configuration, Run 271, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.16 in, YS = 0.00 in, CT = 0.00. ............................ 648

Figure D-213. Baseline configuration, Run 272, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.92°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.............................. 650

Figure D-214. Baseline configuration, Run 273, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 120.00°, XS = 40.16 in, YS = 0.00 in, CT = 0.00............................ 652

Figure D-215. Baseline configuration, Run 0274, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 40.16 in, YS = 0.00 in, CT = 0.00............................ 654

Figure D-216. Baseline configuration, Run 276, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 179.99°, XS = 40.16 in, YS = 0.00 in, CT = 0.00............................ 656

Figure D-217. Baseline configuration, Run 277, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.00°, XS = 40.16 in, YS = 0.00 in, CT = 0.00............................ 658

Figure D-218. Baseline configuration, Run 278, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.96°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.............................. 660

Figure D-219. Baseline configuration, Run 279, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.05°, XS = 40.16 in, YS = 0.00 in, CT = 0.00. ............................ 662

Figure D-220. Baseline configuration, Run 280, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.05°, XS = 40.16 in, YS = 0.00 in, CT = 0.00. ............................ 664

Figure D-221. Baseline configuration, Run 281, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.92°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.............................. 666

Figure D-222. Baseline configuration, Run 282, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.02°, XS = 40.16 in, YS = 0.00 in, CT = 0.00............................ 668

Figure D-223. Baseline configuration, Run 283, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.95°, XS = 40.16 in, YS = 0.00 in, CT = 0.00............................ 670

Figure D-224. Quad-nozzle configuration, Run 288, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.03°, XS = 40.17 in, YS = 0.00 in, CT = 1.92. ............................ 672

Figure D-225. Quad-nozzle configuration, Run 289, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 59.98°, XS = 40.17 in, YS = 0.00 in, CT = 1.93.............................. 674

Figure D-226. Quad-nozzle configuration, Run 290, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 120.04°, XS = 40.17 in, YS = 0.00 in, CT = 1.94............................ 676

Figure D-227. Quad-nozzle configuration, Run 291, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.95°, XS = 40.17 in, YS = 0.00 in, CT = 1.93. ........................ 678

Figure D-228. Quad-nozzle configuration, Run 293, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 179.97°, XS = 40.16 in, YS = 0.00 in, CT = 0.94............................ 680

Figure D-229. Quad-nozzle configuration, Run 294, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 120.02°, XS = 40.16 in, YS = 0.00 in, CT = 0.95............................ 682
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xxiii

Figure D-230. Quad-nozzle configuration, Run 295, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 59.96°, XS = 40.16 in, YS = 0.00 in, CT = 0.95.............................. 684

Figure D-231. Quad-nozzle configuration, Run 296, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.05°, XS = 40.16 in, YS = 0.00 in, CT = 0.94. ............................ 686

Figure D-232. Quad-nozzle configuration, Run 298, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 0.01°, XS = 40.16 in, YS = 0.00 in, CT = 1.92................................ 688

Figure D-233. Quad-nozzle configuration, Run 299, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.92°, XS = 40.16 in, YS = 0.00 in, CT = 1.92.............................. 690

Figure D-234. Quad-nozzle configuration, Run 300, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.02°, XS = 40.16 in, YS = 0.00 in, CT = 1.92............................ 692

Figure D-235. Quad-nozzle configuration, Run 301, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 179.95°, XS = 40.16 in, YS = 0.00 in, CT = 1.93............................ 694

Figure D-236. Quad-nozzle configuration, Run 302, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 179.95°, XS = 40.16 in, YS = 0.00 in, CT = 0.91............................ 696

Figure D-237. Quad-nozzle configuration, Run 303, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 120.08°, XS = 40.16 in, YS = 0.00 in, CT = 0.90............................ 698

Figure D-238. Quad-nozzle configuration, Run 304, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.94°, XS = 40.16 in, YS = 0.00 in, CT = 0.90.............................. 700

Figure D-239. Quad-nozzle configuration, Run 305, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.16 in, YS = 0.00 in, CT = 0.90. ............................ 702

Figure D-240. Quad-nozzle configuration, Run 307, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.05°, XS = 40.17 in, YS = 0.00 in, CT = 1.92................................ 704

Figure D-241. Quad-nozzle configuration, Run 309, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.88°, XS = 40.17 in, YS = 0.00 in, CT = 1.92.............................. 706

Figure D-242. Quad-nozzle configuration, Run 310, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.02°, XS = 40.17 in, YS = 0.00 in, CT = 1.92............................ 708

Figure D-243. Quad-nozzle configuration, Run 311, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −179.99°, XS = 40.17 in, YS = 0.00 in, CT = 1.93. ........................ 710

Figure D-244. Quad-nozzle configuration, Run 312, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −179.97°, XS = 40.17 in, YS = 0.00 in, CT = 0.92. ........................ 712

Figure D-245. Quad-nozzle configuration, Run 313, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.04°, XS = 40.17 in, YS = 0.00 in, CT = 0.92............................ 714

Figure D-246. Quad-nozzle configuration, Run 314, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.98°, XS = 40.17 in, YS = 0.00 in, CT = 0.92.............................. 716

Figure D-247. Quad-nozzle configuration, Run 315, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.05°, XS = 40.17 in, YS = 0.00 in, CT = 0.91................................ 718

Figure E-1. Baseline configuration, Run 013, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.03°, XS = 25.16 in, YS = 0.04 in, CT = 0.00................................ 721

Figure E-2. Baseline configuration, Run 014, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.02°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.............................. 722

Figure E-3. Baseline configuration, Run 016, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 25.16 in, YS = 0.00 in, CT = 0.00................................ 723

Figure E-4. Baseline configuration, Run 017, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.94°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.............................. 724
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xxiv

Figure E-5. Baseline configuration, Run 018, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.90°, XS = 25.16 in, YS = 0.00 in, CT = 0.00............................ 725

Figure E-6. Baseline configuration, Run 019, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.93°, XS = 25.16 in, YS = 0.00 in, CT = 0.00............................ 726

Figure E-7. Baseline configuration, Run 020, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 39.93 in, YS = 0.00 in, CT = 0.00................................ 727

Figure E-8. Baseline configuration, Run 021, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.94°, XS = 39.93 in, YS = 0.00 in, CT = 0.00.............................. 728

Figure E-9. Baseline configuration, Run 022, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 120.00°, XS = 39.93 in, YS = 0.00 in, CT = 0.00............................ 729

Figure E-10. Baseline configuration, Run 023, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 39.93 in, YS = 0.00 in, CT = 0.00............................ 730

Figure E-11. Baseline configuration, Run 024, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 39.93 in, YS = 0.00 in, CT = 0.00................................ 731

Figure E-12. Baseline configuration, Run 025, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.08°, XS = 39.93 in, YS = 0.00 in, CT = 0.00.............................. 732

Figure E-13. Baseline configuration, Run 026, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.03°, XS = 50.17 in, YS = 0.00 in, CT = 0.00................................ 733

Figure E-14. Baseline configuration, Run 027, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.08°, XS = 50.17 in, YS = 0.00 in, CT = 0.00.............................. 734

Figure E-15. Baseline configuration, Run 028, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 120.06°, XS = 50.17 in, YS = 0.00 in, CT = 0.00............................ 735

Figure E-16. Baseline configuration, Run 029, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.91°, XS = 50.17 in, YS = 0.00 in, CT = 0.00............................ 736

Figure E-17. Baseline configuration, Run 030, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.91°, XS = 25.18 in, YS = 0.00 in, CT = 0.00............................ 737

Figure E-18. Baseline configuration, Run 031, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.92°, XS = 25.18 in, YS = 0.00 in, CT = 0.00............................ 738

Figure E-19. Baseline configuration, Run 032, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 25.18 in, YS = 0.00 in, CT = 0.00.............................. 739

Figure E-20. Baseline configuration, Run 033, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 25.18 in, YS = 0.00 in, CT = 0.00................................ 740

Figure E-21. Baseline configuration, Run 034, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 25.18 in, YS = 7.99 in, CT = 0.00................................ 741

Figure E-22. Baseline configuration, Run 035, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.08°, XS = 25.18 in, YS = 7.99 in, CT = 0.00.............................. 742

Figure E-23. Baseline configuration, Run 036, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.90°, XS = 25.18 in, YS = 7.99 in, CT = 0.00............................ 743

Figure E-24. Baseline configuration, Run 037, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 25.18 in, YS = 7.99 in, CT = 0.00............................ 744

Figure E-25. Baseline configuration, Run 038, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.19 in, YS = 7.99 in, CT = 0.00............................ 745

Figure E-26. Baseline configuration, Run 039, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.90°, XS = 40.19 in, YS = 7.99 in, CT = 0.00............................ 746
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xxv

Figure E-27. Baseline configuration, Run 040, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.19 in, YS = 7.99 in, CT = 0.00.............................. 747

Figure E-28. Baseline configuration, Run 041, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 40.19 in, YS = 7.99 in, CT = 0.00................................ 748

Figure E-29. Baseline configuration, Run 042, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.19 in, YS = −8.00 in, CT = 0.00. .......................... 749

Figure E-30. Baseline configuration, Run 043, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.92°, XS = 40.19 in, YS = −8.00 in, CT = 0.00. .......................... 750

Figure E-31. Baseline configuration, Run 044, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.90°, XS = 40.19 in, YS = –8.00 in, CT = 0.00.......................... 751

Figure E-32. Baseline configuration, Run 045, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.19 in, YS = –8.00 in, CT = 0.00.......................... 752

Figure E-33. Baseline configuration, Run 046, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 50.16 in, YS = –8.00 in, CT = 0.00.......................... 753

Figure E-34. Baseline configuration, Run 047, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.92°, XS = 50.16 in, YS = –8.00 in, CT = 0.00.......................... 754

Figure E-35. Baseline configuration, Run 048, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 50.16 in, YS = –8.00 in, CT = 0.00............................ 755

Figure E-36. Baseline configuration, Run 049, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 50.16 in, YS = –8.00 in, CT = 0.00.............................. 756

Figure E-37. Baseline configuration, Run 050, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.02°, XS = 50.16 in, YS = 0.00 in, CT = 0.00.............................. 757

Figure E-38. Baseline configuration, Run 051, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.94°, XS = 50.16 in, YS = 0.00 in, CT = 0.00............................ 758

Figure E-39. Baseline configuration, Run 052, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 50.16 in, YS = 0.00 in, CT = 0.00............................ 759

Figure E-40. Baseline configuration, Run 053, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 39.93 in, YS = 0.00 in, CT = 0.00................................ 760

Figure E-41. Baseline configuration, Run 054, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.06°, XS = 40.17 in, YS = 0.00 in, CT = 0.00............................ 761

Figure E-42. Baseline configuration, Run 055, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.17 in, YS = 0.00 in, CT = 0.00.............................. 762

Figure E-43. Baseline configuration, Run 056, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.07°, XS = 40.17 in, YS = 0.00 in, CT = 0.00. ............................ 763

Figure E-44. Baseline configuration, Run 057, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.07°, XS = 25.16 in, YS = 0.00 in, CT = 0.00. ............................ 764

Figure E-45. Baseline configuration, Run 058, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.04°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.............................. 765

Figure E-46. Baseline configuration, Run 059, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.06°, XS = 25.16 in, YS = 0.00 in, CT = 0.00............................ 766

Figure E-47. Baseline configuration, Run 060, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 25.16 in, YS = 0.00 in, CT = 0.00............................ 767

Figure E-48. Baseline configuration, Run 065, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 25.16 in, YS = −8.00 in, CT = 0.00. .......................... 768
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xxvi

Figure E-49. Baseline configuration, Run 067, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.06°, XS = 25.16 in, YS = –8.00 in, CT = 0.00............................ 769

Figure E-50. Baseline configuration, Run 068, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.96°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.......................... 770

Figure E-51. Baseline configuration, Run 069, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.......................... 771

Figure E-52. Baseline configuration, Run 070, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.16 in, YS = –8.00 in, CT = 0.00.......................... 772

Figure E-53. Baseline configuration, Run 073, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.92°, XS = 40.18 in, YS = –8.00 in, CT = 0.00.......................... 773

Figure E-54. Baseline configuration, Run 074, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.02°, XS = 40.18 in, YS = –8.00 in, CT = 0.00............................ 774

Figure E-55. Baseline configuration, Run 075, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.03°, XS = 40.18 in, YS = –8.00 in, CT = 0.00.............................. 775

Figure E-56. Baseline configuration, Run 076, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.03°, XS = 40.18 in, YS = 7.99 in, CT = 0.00................................ 776

Figure E-57. Baseline configuration, Run 077, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.16 in, YS = 7.99 in, CT = 0.00.............................. 777

Figure E-58. Baseline configuration, Run 078, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.92°, XS = 40.16 in, YS = 7.95 in, CT = 0.00............................ 778

Figure E-59. Baseline configuration, Run 079, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −179.99°, XS = 40.16 in, YS = 7.95 in, CT = 0.00. ........................ 779

Figure E-60. Baseline configuration, Run 080, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −179.99°, XS = 50.15 in, YS = 7.95 in, CT = 0.00. ........................ 780

Figure E-61. Baseline configuration, Run 081, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.92°, XS = 50.15 in, YS = 7.95 in, CT = 0.00............................ 781

Figure E-62. Baseline configuration, Run 082, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.00°, XS = 50.15 in, YS = 7.95 in, CT = 0.00.............................. 782

Figure E-63. Baseline configuration, Run 083, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 50.15 in, YS = 7.95 in, CT = 0.00................................ 783

Figure E-64. Baseline configuration, Run 086, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 0.01°, XS = 25.17 in, YS = 0.00 in, CT = 0.00................................ 784

Figure E-65. Baseline configuration, Run 087, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 60.04°, XS = 25.17 in, YS = 0.00 in, CT = 0.00.............................. 785

Figure E-66. Baseline configuration, Run 088, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 119.90°, XS = 25.17 in, YS = 0.00 in, CT = 0.00............................ 786

Figure E-67. Baseline configuration, Run 089, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 179.91°, XS = 25.17 in, YS = 0.00 in, CT = 0.00............................ 787

Figure E-68. Baseline configuration, Run 090, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.00................................ 788

Figure E-69. Baseline configuration, Run 091, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 60.00°, XS = 40.18 in, YS = 0.00 in, CT = 0.00.............................. 789

Figure E-70. Baseline configuration, Run 092, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 119.92°, XS = 40.18 in, YS = 0.00 in, CT = 0.00............................ 790
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xxvii

Figure E-71. Baseline configuration, Run 093, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 179.91°, XS = 40.18 in, YS = 0.00 in, CT = 0.00............................ 791

Figure E-72. Baseline configuration, Run 094, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 179.91°, XS = 50.14 in, YS = 0.00 in, CT = 0.00............................ 792

Figure E-73. Baseline configuration, Run 095, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 119.90°, XS = 50.14 in, YS = 0.00 in, CT = 0.00............................ 793

Figure E-74. Baseline configuration, Run 096, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 59.96°, XS = 50.14 in, YS = 0.00 in, CT = 0.00.............................. 794

Figure E-75. Baseline configuration, Run 097, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = −0.07°, XS = 50.14 in, YS = 0.00 in, CT = 0.00. ............................ 795

Figure E-76. Baseline configuration, Run 098, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = −0.07°, XS = 50.14 in, YS = 7.99 in, CT = 0.00. ............................ 796

Figure E-77. Baseline configuration, Run 099, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 59.92°, XS = 50.14 in, YS = 7.99 in, CT = 0.00.............................. 797

Figure E-78. Baseline configuration, Run 100, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 120.00°, XS = 50.14 in, YS = 7.99 in, CT = 0.00............................ 798

Figure E-79. Baseline configuration, Run 101, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 179.97°, XS = 50.14 in, YS = 7.99 in, CT = 0.00............................ 799

Figure E-80. Baseline configuration, Run 104, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.03°, XS = 25.19 in, YS = 0.00 in, CT = 0.00. ............................ 800

Figure E-81. Baseline configuration, Run 105, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 60.00°, XS = 25.19 in, YS = 0.00 in, CT = 0.00.............................. 801

Figure E-82. Baseline configuration, Run 106, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.96°, XS = 25.19 in, YS = 0.00 in, CT = 0.00............................ 802

Figure E-83. Baseline configuration, Run 107, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.93°, XS = 25.19 in, YS = 0.00 in, CT = 0.00............................ 803

Figure E-84. Baseline configuration, Run 108, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.93°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 804

Figure E-85. Baseline configuration, Run 109, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.92°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 805

Figure E-86. Baseline configuration, Run 110, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 59.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.............................. 806

Figure E-87. Baseline configuration, Run 111, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.01°, XS = 40.09 in, YS = 0.00 in, CT = 0.00. ............................ 807

Figure E-88. Baseline configuration, Run 112, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.01°, XS = 50.19 in, YS = 0.00 in, CT = 0.00. ............................ 808

Figure E-89. Baseline configuration, Run 113, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 60.02°, XS = 50.19 in, YS = 0.00 in, CT = 0.00.............................. 809

Figure E-90. Baseline configuration, Run 114, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 120.04°, XS = 50.19 in, YS = 0.00 in, CT = 0.00............................ 810

Figure E-91. Baseline configuration, Run 115, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.97°, XS = 50.19 in, YS = 0.00 in, CT = 0.00............................ 811

Figure E-92. Baseline configuration, Run 116, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.97°, XS = 50.19 in, YS = 8.00 in, CT = 0.00............................ 812
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xxviii

Figure E-93. Baseline configuration, Run 117, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.92°, XS = 50.19 in, YS = 8.00 in, CT = 0.00............................ 813

Figure E-94. Baseline configuration, Run 118, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 59.96°, XS = 50.19 in, YS = 8.00 in, CT = 0.00.............................. 814

Figure E-95. Baseline configuration, Run 119, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.03°, XS = 50.19 in, YS = 8.00 in, CT = 0.00................................ 815

Figure E-96. Baseline configuration, Run 120, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.03°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.............................. 816

Figure E-97. Baseline configuration, Run 121, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 60.06°, XS = 25.16 in, YS = –8.00 in, CT = 0.00............................ 817

Figure E-98. Baseline configuration, Run 122, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 120.00°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.......................... 818

Figure E-99. Baseline configuration, Run 123, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.91°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.......................... 819

Figure E-100. Center nozzle configuration, Run 136, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = –0.01°, XS = 40.16 in, YS = 0.00 in, CT = 4.03.............................. 820

Figure E-101. Center nozzle configuration, Run 137, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 2.99. ............................ 821

Figure E-102. Center nozzle configuration, Run 138, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 3.01............................ 822

Figure E-103. Center nozzle configuration, Run 139, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 0.97............................ 823

Figure E-104. Center nozzle configuration, Run 140, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = –0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.97.............................. 824

Figure E-105. Center nozzle configuration, Run 141, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 1.98. ............................ 825

Figure E-106. Center nozzle configuration, Run 142, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.91°, XS = 40.15 in, YS = 0.00 in, CT = 1.99. ........................ 826

Figure E-107. Center nozzle configuration, Run 143, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.91°, XS = 40.15 in, YS = 0.00 in, CT = 0.46. ........................ 827

Figure E-108. Center nozzle configuration, Run 144, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.47................................ 828

Figure E-109. Center nozzle configuration, Run 145, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.23................................ 829

Figure E-110. Center nozzle configuration, Run 146, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.23............................ 830

Figure E-111. Center nozzle configuration, Run 147, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −180.00°, XS = 40.15 in, YS = 0.00 in, CT = 0.19. ........................ 831

Figure E-112. Center nozzle configuration, Run 148, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 832

Figure E-113. Center nozzle configuration, Run 149, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.00. ............................ 833

Figure E-114. Center nozzle configuration, Run 150, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.17 in, YS = 0.00 in, CT = 2.99. ............................ 834
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xxix

Figure E-115. Center nozzle configuration, Run 151, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −179.97°, XS = 40.17 in, YS = 0.00 in, CT = 3.01. ........................ 835

Figure E-116. Center nozzle configuration, Run 152, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −179.97°, XS = 40.17 in, YS = 0.00 in, CT = 1.95. ........................ 836

Figure E-117. Center nozzle configuration, Run 153, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.09°, XS = 40.17 in, YS = 0.00 in, CT = 1.96. ............................ 837

Figure E-118. Center nozzle configuration, Run 154, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.09°, XS = 40.17 in, YS = 0.00 in, CT = 0.94. ............................ 838

Figure E-119. Center nozzle configuration, Run 155, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.91°, XS = 40.17 in, YS = 0.00 in, CT = 0.95............................ 839

Figure E-120. Center nozzle configuration, Run 156, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.93°, XS = 40.17 in, YS = 0.00 in, CT = 0.45............................ 840

Figure E-121. Center nozzle configuration, Run 157, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.07°, XS = 40.17 in, YS = 0.00 in, CT = 0.45................................ 841

Figure E-122. Center nozzle configuration, Run 159, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.17 in, YS = 0.00 in, CT = 0.21. ............................ 842

Figure E-123. Center nozzle configuration, Run 160, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.93°, XS = 40.17 in, YS = 0.00 in, CT = 0.21............................ 843

Figure E-124. Center nozzle configuration, Run 161, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.93°, XS = 40.17 in, YS = 0.00 in, CT = 0.00............................ 844

Figure E-125. Center nozzle configuration, Run 162, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.03°, XS = 40.17 in, YS = 0.00 in, CT = 0.00................................ 845

Figure E-126. Center nozzle configuration, Run 163, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.03°, XS = 40.17 in, YS = 0.00 in, CT = 2.92................................ 846

Figure E-127. Center nozzle configuration, Run 164, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 1479.91°, XS = 40.17 in, YS = 0.00 in, CT = 2.91.......................... 847

Figure E-128. Center nozzle configuration, Run 165, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.93°, XS = 40.15 in, YS = 0.00 in, CT = 1.93............................ 848

Figure E-129. Center nozzle configuration, Run 166, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.03°, XS = 40.15 in, YS = 0.00 in, CT = 1.96................................ 849

Figure E-130. Center nozzle configuration, Run 167, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.94................................ 850

Figure E-131. Center nozzle configuration, Run 168, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.96............................ 851

Figure E-132. Center nozzle configuration, Run 169, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.45............................ 852

Figure E-133. Center nozzle configuration, Run 170, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.46................................ 853

Figure E-134. Center nozzle configuration, Run 171, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.22................................ 854

Figure E-135. Center nozzle configuration, Run 172, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.91°, XS = 40.15 in, YS = 0.00 in, CT = 0.22............................ 855

Figure E-136. Center nozzle configuration, Run 173, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.91°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 856
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xxx

Figure E-137. Center nozzle configuration, Run 174, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.07°, XS = 40.15 in, YS = 0.00 in, CT = 0.00. ............................ 857

Figure E-138. Tri-nozzle configuration, Run 179, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.09°, XS = 40.15 in, YS = 0.00 in, CT = 2.95................................ 858

Figure E-139. Tri-nozzle configuration, Run 180, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.00. ............................ 859

Figure E-140. Tri-nozzle configuration, Run 181, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 860

Figure E-141. Tri-nozzle configuration, Run 182, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.96°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 861

Figure E-142. Tri-nozzle configuration, Run 183, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.04°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.............................. 862

Figure E-143. Tri-nozzle configuration, Run 184, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.00................................ 863

Figure E-144. Tri-nozzle configuration, Run 185, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 59.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.............................. 864

Figure E-145. Tri-nozzle configuration, Run 186, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 865

Figure E-146. Tri-nozzle configuration, Run 187, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 866

Figure E-147. Tri-nozzle configuration, Run 190, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 2.95. ............................ 867

Figure E-148. Tri-nozzle configuration, Run 191, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 58.37°, XS = 40.15 in, YS = 0.00 in, CT = 2.95.............................. 868

Figure E-149. Tri-nozzle configuration, Run 192, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.94°, XS = 40.15 in, YS = 0.00 in, CT = 2.93............................ 869

Figure E-150. Tri-nozzle configuration, Run 193, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.97°, XS = 40.15 in, YS = 0.00 in, CT = 2.95. ........................ 870

Figure E-151. Tri-nozzle configuration, Run 194, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.97°, XS = 40.15 in, YS = 0.00 in, CT = 1.94. ........................ 871

Figure E-152. Tri-nozzle configuration, Run 195, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.96°, XS = 40.15 in, YS = 0.00 in, CT = 1.93............................ 872

Figure E-153. Tri-nozzle configuration, Run 196, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.94°, XS = 40.15 in, YS = 0.00 in, CT = 1.93.............................. 873

Figure E-154. Tri-nozzle configuration, Run 197, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 1.93. ............................ 874

Figure E-155. Tri-nozzle configuration, Run 198, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.95. ............................ 875

Figure E-156. Tri-nozzle configuration, Run 199, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.15 in, YS = 0.00 in, CT = 0.94.............................. 876

Figure E-157. Tri-nozzle configuration, Run 200, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.94............................ 877

Figure E-158. Tri-nozzle configuration, Run 201, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.94............................ 878
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xxxi

Figure E-159. Tri-nozzle configuration, Run 202, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.43............................ 879

Figure E-160. Tri-nozzle configuration, Run 203, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.97°, XS = 40.15 in, YS = 0.00 in, CT = 0.44. ........................ 880

Figure E-161. Tri-nozzle configuration, Run 204, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.98°, XS = 40.15 in, YS = 0.00 in, CT = 0.44............................ 881

Figure E-162. Tri-nozzle configuration, Run 205, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.43.............................. 882

Figure E-163. Tri-nozzle configuration, Run 206, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.43. ............................ 883

Figure E-164. Tri-nozzle configuration, Run 211, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 2.94. ............................ 884

Figure E-165. Tri-nozzle configuration, Run 212, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 60.02°, XS = 40.15 in, YS = 0.00 in, CT = 2.93.............................. 885

Figure E-166. Tri-nozzle configuration, Run 213, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.98°, XS = 40.15 in, YS = 0.00 in, CT = 2.95............................ 886

Figure E-167. Tri-nozzle configuration, Run 214, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 2.95............................ 887

Figure E-168. Tri-nozzle configuration, Run 217, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.48. ............................ 888

Figure E-169. Tri-nozzle configuration, Run 218, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.48.............................. 889

Figure E-170. Tri-nozzle configuration, Run 219, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.96°, XS = 40.15 in, YS = 0.00 in, CT = 0.48............................ 890

Figure E-171. Tri-nozzle configuration, Run 220, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.48............................ 891

Figure E-172. Tri-nozzle configuration, Run 221, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.23. ............................ 892

Figure E-173. Tri-nozzle configuration, Run 222, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 2.95. ............................ 893

Figure E-174. Tri-nozzle configuration, Run 223, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 59.96°, XS = 40.15 in, YS = 0.00 in, CT = 2.94.............................. 894

Figure E-175. Tri-nozzle configuration, Run 224, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.00°, XS = 40.15 in, YS = 0.00 in, CT = 3.00............................ 895

Figure E-176. Tri-nozzle configuration, Run 225, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 2.98............................ 896

Figure E-177. Tri-nozzle configuration, Run 226, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 1.96............................ 897

Figure E-178. Tri-nozzle configuration, Run 227, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.98°, XS = 40.15 in, YS = 0.00 in, CT = 1.94............................ 898

Figure E-179. Tri-nozzle configuration, Run 228, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.02°, XS = 40.15 in, YS = 0.00 in, CT = 1.94.............................. 899

Figure E-180. Tri-nozzle configuration, Run 229, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 1.95. ............................ 900
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xxxii

Figure E-181. Tri-nozzle configuration, Run 230, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.97. ............................ 901

Figure E-182. Tri-nozzle configuration, Run 233, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 59.96°, XS = 40.15 in, YS = 0.00 in, CT = 0.96.............................. 902

Figure E-183. Tri-nozzle configuration, Run 234, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.97. ............................ 903

Figure E-184. Tri-nozzle configuration, Run 235, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.00°, XS = 40.15 in, YS = 0.00 in, CT = 0.96............................ 904

Figure E-185. Tri-nozzle configuration, Run 236, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.96............................ 905

Figure E-186. Tri-nozzle configuration, Run 237, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.47............................ 906

Figure E-187. Tri-nozzle configuration, Run 238, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.47............................ 907

Figure E-188. Tri-nozzle configuration, Run 239, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.00°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.............................. 908

Figure E-189. Tri-nozzle configuration, Run 240, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.46. ............................ 909

Figure E-190. Tri-nozzle configuration, Run 241, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.22. ............................ 910

Figure E-191. Tri-nozzle configuration, Run 242, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 1.96. ............................ 911

Figure E-192. Tri-nozzle configuration, Run 243, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 60.00°, XS = 40.15 in, YS = 0.00 in, CT = 1.95.............................. 912

Figure E-193. Tri-nozzle configuration, Run 244, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 120.00°, XS = 40.15 in, YS = 0.00 in, CT = 1.96............................ 913

Figure E-194. Tri-nozzle configuration, Run 245, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −179.99°, XS = 40.15 in, YS = 0.00 in, CT = 1.97. ........................ 914

Figure E-195. Tri-nozzle configuration, Run 247, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 1.92. ............................ 915

Figure E-196. Tri-nozzle configuration, Run 248, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 1.93............................ 916

Figure E-197. Tri-nozzle configuration, Run 249, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.90............................ 917

Figure E-198. Tri-nozzle configuration, Run 250, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.96°, XS = 40.15 in, YS = 0.00 in, CT = 0.90............................ 918

Figure E-199. Tri-nozzle configuration, Run 251, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 60.04°, XS = 40.15 in, YS = 0.00 in, CT = 0.90.............................. 919

Figure E-200. Tri-nozzle configuration, Run 252, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.90. ............................ 920

Figure E-201. Tri-nozzle configuration, Run 253, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.42. ............................ 921

Figure E-202. Tri-nozzle configuration, Run 254, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 60.00°, XS = 40.15 in, YS = 0.00 in, CT = 0.42.............................. 922
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xxxiii

Figure E-203. Tri-nozzle configuration, Run 255, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.96°, XS = 40.15 in, YS = 0.00 in, CT = 0.42............................ 923

Figure E-204. Tri-nozzle configuration, Run 256, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.43............................ 924

Figure E-205. Tri-nozzle configuration, Run 257, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.20. ............................ 925

Figure E-206. Tri-nozzle configuration, Run 258, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.00. ............................ 926

Figure E-207. Tri-nozzle configuration, Run 259, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 59.96°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.............................. 927

Figure E-208. Tri-nozzle configuration, Run 260, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 928

Figure E-209. Tri-nozzle configuration, Run 261, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.00............................ 929

Figure E-210. Tri-nozzle configuration, Run 262, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.01°, XS = 40.15 in, YS = 0.00 in, CT = 2.94................................ 930

Figure E-211. Tri-nozzle configuration, Run 263, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −179.99°, XS = 40.15 in, YS = 0.00 in, CT = 2.93. ........................ 931

Figure E-212. Tri-nozzle configuration, Run 264, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 5.95............................ 932

Figure E-213. Tri-nozzle configuration, Run 265, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.91. ............................ 933

Figure E-214. Tri-nozzle configuration, Run 266, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.45. ............................ 934

Figure E-215. Tri-nozzle configuration, Run 267, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 4.95. ............................ 935

Figure E-216. Baseline configuration, Run 271, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.16 in, YS = 0.00 in, CT = 0.00. ............................ 936

Figure E-217. Baseline configuration, Run 272, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.............................. 937

Figure E-218. Baseline configuration, Run 273, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.94°, XS = 40.16 in, YS = 0.00 in, CT = 0.00............................ 938

Figure E-219. Baseline configuration, Run 0274, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 40.16 in, YS = 0.00 in, CT = 0.00............................ 939

Figure E-220. Baseline configuration, Run 276, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 40.16 in, YS = 0.00 in, CT = 0.00............................ 940

Figure E-221. Baseline configuration, Run 277, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.94°, XS = 40.16 in, YS = 0.00 in, CT = 0.00............................ 941

Figure E-222. Baseline configuration, Run 278, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.00°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.............................. 942

Figure E-223. Baseline configuration, Run 279, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.16 in, YS = 0.00 in, CT = 0.00. ............................ 943

Figure E-224. Baseline configuration, Run 280, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.05°, XS = 40.16 in, YS = 0.00 in, CT = 0.00. ............................ 944
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xxxiv

Figure E-225. Baseline configuration, Run 281, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 59.98°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.............................. 945

Figure E-226. Baseline configuration, Run 282, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.96°, XS = 40.16 in, YS = 0.00 in, CT = 0.00............................ 946

Figure E-227. Baseline configuration, Run 283, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.97°, XS = 40.16 in, YS = 0.00 in, CT = 0.00............................ 947

Figure E-228. Quad-nozzle configuration, Run 288, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.17 in, YS = 0.00 in, CT = 1.92. ............................ 948

Figure E-229. Quad-nozzle configuration, Run 289, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.17 in, YS = 0.00 in, CT = 1.93.............................. 949

Figure E-230. Quad-nozzle configuration, Run 290, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.98°, XS = 40.17 in, YS = 0.00 in, CT = 1.93............................ 950

Figure E-231. Quad-nozzle configuration, Run 291, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.95°, XS = 40.17 in, YS = 0.00 in, CT = 1.94. ........................ 951

Figure E-232. Quad-nozzle configuration, Run 292, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 149.95°, XS = 40.16 in, YS = 0.00 in, CT = 1.93............................ 952

Figure E-233. Quad-nozzle configuration, Run 293, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.16 in, YS = 0.00 in, CT = 0.94............................ 953

Figure E-234. Quad-nozzle configuration, Run 294, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.96°, XS = 40.16 in, YS = 0.00 in, CT = 0.95............................ 954

Figure E-235. Quad-nozzle configuration, Run 295, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.02°, XS = 40.16 in, YS = 0.00 in, CT = 0.94.............................. 955

Figure E-236. Quad-nozzle configuration, Run 296, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.16 in, YS = 0.00 in, CT = 0.95. ............................ 956

Figure E-237. Quad-nozzle configuration, Run 297, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 30.03°, XS = 40.15 in, YS = 0.00 in, CT = 2.95.............................. 957

Figure E-238. Quad-nozzle configuration, Run 298, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 40.16 in, YS = 0.00 in, CT = 1.91................................ 958

Figure E-239. Quad-nozzle configuration, Run 299, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.16 in, YS = 0.00 in, CT = 1.92.............................. 959

Figure E-240. Quad-nozzle configuration, Run 300, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.96°, XS = 40.16 in, YS = 0.00 in, CT = 1.92............................ 960

Figure E-241. Quad-nozzle configuration, Run 301, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.16 in, YS = 0.00 in, CT = 1.92............................ 961

Figure E-242. Quad-nozzle configuration, Run 302, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.16 in, YS = 0.00 in, CT = 0.90............................ 962

Figure E-243. Quad-nozzle configuration, Run 303, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.02°, XS = 40.16 in, YS = 0.00 in, CT = 0.89............................ 963

Figure E-244. Quad-nozzle configuration, Run 304, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.00°, XS = 40.16 in, YS = 0.00 in, CT = 0.90.............................. 964

Figure E-245. Quad-nozzle configuration, Run 305, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.16 in, YS = 0.00 in, CT = 0.90. ............................ 965

Figure E-246. Quad-nozzle configuration, Run 306, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 29.99°, XS = 40.17 in, YS = 0.00 in, CT = 2.92.............................. 966
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xxxv

Figure E-247. Quad-nozzle configuration, Run 307, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.05°, XS = 40.17 in, YS = 0.00 in, CT = 1.93................................ 967

Figure E-248. Quad-nozzle configuration, Run 309, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 59.94°, XS = 40.17 in, YS = 0.00 in, CT = 1.92.............................. 968

Figure E-249. Quad-nozzle configuration, Run 310, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.96°, XS = 40.17 in, YS = 0.00 in, CT = 1.92............................ 969

Figure E-250. Quad-nozzle configuration, Run 311, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −179.97°, XS = 40.17 in, YS = 0.00 in, CT = 1.92. ........................ 970

Figure E-251. Quad-nozzle configuration, Run 312, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −179.97°, XS = 40.17 in, YS = 0.00 in, CT = 0.91. ........................ 971

Figure E-252. Quad-nozzle configuration, Run 313, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.98°, XS = 40.17 in, YS = 0.00 in, CT = 0.92............................ 972

Figure E-253. Quad-nozzle configuration, Run 314, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 60.04°, XS = 40.17 in, YS = 0.00 in, CT = 0.91.............................. 973

Figure E-254. Quad-nozzle configuration, Run 315, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.05°, XS = 40.17 in, YS = 0.00 in, CT = 0.92................................ 974

Figure E-255. Center nozzle configuration, Run 319, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 37.47 in, YS = 0.00 in, CT = 0.45................................ 975

Figure E-256. Center nozzle configuration, Run 320, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 43.35 in, YS = 0.00 in, CT = 1.96................................ 976

Figure E-257. Center nozzle configuration, Run 321, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.01°, XS = 42.98 in, YS = 0.00 in, CT = 1.96................................ 977
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

xxxvi

NOMENCLATURE

Symbols

Aref forebody reference area, ft2

Cp pressure coefficient

CT thrust coefficient

D diameter, in

L model length used to normalize longitudinal distance on the model, in

M Mach number 

P pressure, psia or psf

q dynamic pressure, psf

Re unit Reynolds number, ft–1

R forebody radius used to normalize radial distance on the model, in

r, θ model polar coordinates, defined in figure 11

T temperature, deg F or R

V velocity, ft/sec

x, y, z model Cartesian coordinates

X, Y, Z tunnel Cartesian coordinates, defined in figure 5

α model angle of attack, deg

 model angle of yaw, deg

φ model roll angle, deg

ρ density, slug/ft3

Subscripts

j conditions within the nozzle jet

S strut position

T stagnation

∞ free-stream conditions

Acronyms

A/D analog-to-digital

AMS angle measurement system

CFD computational fluid dynamics

DCV digital control valve

DWG drawing

EDL entry, descent, and landing

ESP electronically scanned pressure

fps frames per second

LaRC Langley Research Center

NASA National Aeronautics and Space Administration

RTD resistance temperature detector

SRP supersonic retropropulsion

UPWT Unitary Plan Wind Tunnel

ViDI Virtual Diagnostics Interface
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

1

 SECTION 1

INTRODUCTION

Present capability for entry, descent, and landing (EDL) of small robotic missions to Mars, 

typified by a landed mass less than a metric ton, is predicated on the use of parachutes for a 

significant portion of the deceleration required to safely reach the surface. Practically speaking,

this approach is not scalable to larger payloads because of physical limits with parachute size, 

materials, and testing capabilities. A proposed alternate approach is to use propulsive 

deceleration earlier in the trajectory, taking advantage of engines, typically required for landing,

while still flying supersonically. Thus, supersonic retropropulsion (SRP), or the use of engine 

thrust directed towards the oncoming supersonic free-stream flow to slow down, is deemed a 

potentially enabling technology for future large payload missions to Mars (such as human 

exploration missions that would be on the order of tens of metric tons) and is a present focus of 

the EDL community. For further discussions of SRP from a systems analysis and performance 

perspective (see ref. 1–5). A broader survey of the literature is provided in reference 6. 

To date, only a handful of studies have been conducted for understanding the fluid dynamics

phenomena associated with the use of SRP, and most of those were performed decades ago, for 

an example see reference 7. These older studies were typically exploratory in nature, designed to 

investigate the aerodynamic behavior of various representative Mars EDL SRP configurations. 

While useful for providing insights into the complex interaction between a supersonic free 

stream and an opposing rocket plume, shown notionally in figure 1 for a single nozzle, the 

historical reports have not retained enough detail for meaningful comparisons against modern 

computational fluid dynamics (CFD) codes (ref. 8). For instance, while static aerodynamic 

response characteristics are reported, the dynamics of the interactions are often neither discussed 

nor captured in the still images and time averaged data. Thus, there is a need for modern SRP 

experiments, designed to provide higher fidelity datasets specifically for CFD comparisons. 

With potential for multi-phased and unsteady plumes, and large scale separations and turbulence, 

SRP represents an extremely complex and challenging problem for use as a test case for 

assessing CFD modeling strengths and weaknesses, as discussed in references 8 and 9. Other 

recent reports that also provide comparisons of computational solutions against the historical 

data include references 10–15.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

2

Figure 1. Conceptual sketch of SRP flow features.

Figure 1 provides the salient flowfield features associated with supersonic retropropulsion, which 

is characterized by a bow shock that is pushed further away from the body via the addition of the 

jet flow emanating from the nozzles. For the simple case of a single nozzle with sufficient 

backpressure, the exiting supersonic jet forms a barrel shock and corresponding shear layer that 

is terminated by a Mach disk as the jet flow decelerates to subsonic conditions because of the 

oncoming flow. The intersection of the barrel shock and Mach disk forms the triple point, an 

annular region that represents the terminus of the jet plume. The boundary between the two 

flowfields, the oncoming free stream and opposing jet flow, establishes an “effective body” that 

represents a new “virtual” entry body shape. A point exists on this effective body at which both 

flowfields stagnate typically just in front of the Mach disk. The fluidic nature of the effective 

body suggests dynamic behavior, but the level of unsteadiness and/or impact for a future flight 

system is not established by the historical data. 

Past SRP experiments have established that for a given configuration two distinct flowfield 

modes can result, depending on the nozzle backpressure. For high nozzle chamber pressures, a 

short, wide jet plume (as depicted in figure 1) is formed that tends to be fairly stable. This case 

is typically referred to as blunt penetration mode, resulting in jet plumes that globally push the 

bow shock away from the body. The other end of the backpressure spectrum results in narrow 

and elongated plumes that appear to penetrate the bow shock. In this case, typically referred to 

as long penetration mode, the jet plumes only locally displace the bow shock, resulting in a more 

dynamic and unstable flowfield. Reference 16 provides further discussion of the transition 

between these two regimes. From a future flight system perspective, high mass missions would 

likely require high thrust and thus high nozzle chamber pressures, taking advantage of the 

relative stability of the blunt penetration mode.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

3

The present report provides details of an experimental SRP study conducted in 2010 in the 

National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC)

Unitary Plan Wind Tunnel (UPWT). The primary objective of this study was to conduct a 

validation experiment in support of improved CFD models and capabilities. Thus, both 

experimentalists and computationalists were heavily engaged in all aspects of the design of the

wind tunnel model and execution of the experiment, a recommendation of reference 17. As a 

validation experiment, the forebody was heavily instrumented with surface pressure ports, with 

modules internal to the model to minimize pressure response issues. Also, a few fast response 

pressure gages were included to monitor forebody surface pressure fluctuations. A high speed 

video camera was used to capture the dynamics of the interactions between the bow shock and 

jet plume. Pretest CFD solutions were used to size the model within the test core to minimize 

tunnel interference effects. Internal flow computations also pointed to concerns over potential 

liquefaction within the nozzle plumes. To mitigate the need for computing multiphase flows, the 

decision was made to preheat the high pressure air leading into the plenum. This necessitated a 

heat conduction analysis of the model assembly to insure the internal pressure modules did not 

exceed their safe operating conditions and led to the addition of an insulating barrier between the 

plenum and modules. In addition, Virtual Diagnostics Interface (ViDI) simulations (ref. 18) 

were conducted of the movement of the tunnel’s angle of attack mechanism in pitch, yaw, roll,

and translation within the tunnel. These simulations were completed to assess the allowable

range of the model (with a notional plume structure) movement within the tunnel test core in 

support of the run matrix development. The widest reasonable range of movement was required 

to allow quantification of measurement uncertainty (in a manner similar to ref. 17). Model 

design and test development aspects are also discussed in reference 19, and preliminary 

experimental results are presented in reference 20. The present report provides details of the 

experiment, a discussion of the trends observed, as well as a compendium of the schlieren and 

surface pressure results. High frequency results and analysis are presented in reference 21. The 

derived uncertainty results and analysis are presented in reference 22.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

4

 SECTION 2

APPARATUS AND METHODS

2.1 Facility

The NASA LaRC UPWT is a closed circuit continuous flow pressure tunnel with two test 

sections that are nominally 4-ft by 4-ft in cross section and 7 feet long. A photograph of the 

building that houses this test complex is shown in figure 2 (ref. 23). The primary elements of the 

UPWT are a 100,000-horsepower compressor-drive system, a dry air supply and evacuating 

system, a cooling system, and interconnecting tubes that allow air circulation through either of 

the two test sections. A general layout that highlights these facility elements is illustrated in

figure 3 (ref. 23). The Mach number range is 1.50 to 2.86 in Test Section 1 and 2.30 to 4.63 in 

Test Section 2. The stagnation pressure can be varied up to a maximum of 50 psia in Test 

Section 1 and 100 psia in Test Section 2. Each test section has an asymmetric sliding-block type 

nozzle that accelerates the flow to supersonic conditions within the test section. The Mach 

number within the test section is varied by moving the lower sliding block, which alters the

nozzle-throat-to-test-section area ratio. Figure 4 provides a sketch of the sliding-block nozzle 

concept, while the test section and model support system are shown in figure 5 (ref. 23). The 

second minimum area downstream of the test section is controlled by hinged sidewalls that 

provide the required constriction for stabilizing the posttest section normal shock for the various 

operating Mach numbers. The most recent calibration of the tunnel (from 1981) is provided in 

reference 24 while reference 25 provides details for planning a test within the UPWT.

Figure 2. The Unitary Plan Wind Tunnel complex in Building 1251 at NASA 

Langley Research Center (ref. 23).
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

5

Figure 3. Schematic of the NASA LaRC Unitary Plan Wind Tunnel 

complex (ref. 23).

Figure 4. Schematic of the UPWT Test Section 2 nozzle block (ref. 23).
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

6

Figure 5. Test Section 2 model support system (ref. 23).

Test Section 2 was used exclusively for this study, as this leg provided the Mach numbers of 

interest identified by recent system level trade studies (ref. 3 and 5). Thus, all subsequent facility 

discussion will focus on the capabilities of the higher Mach number leg. The facility has six 

centrifugal compressors that are used in specific combinations, or modes, depending on the

desired Mach number. For each mode, or Mach number range, the upper limit of the operating 

envelope is established by the drive system power and the stagnation pressure limit, while the 

lower limit is dictated by the supersonic-flow stability characteristics at reduced pressure. 

Typical unit Reynolds numbers for testing in the UPWT Test Section 2 are 1 to 5 million per 

foot. The tunnel stagnation temperatures are typically 125 or 150°F depending on the mode of 

operation.

The standard Test Section 2 model mounting hardware was used for this test, as shown in figure 

5. The basic mechanism is the horizontal wall mounted strut that is capable of forward and aft 

travel (in the x direction) of up to 36.25 in. Attached to this strut is a sting support that allows 

lateral traverse (in the y direction) of ±20 in and sideslip motion ±12 degrees. Forward of the 

sting support are the angle of attack () and roll mechanisms, which provide a pitch range of –15

to 30 degrees and a range of roll of up to 357 degrees. 

An upgraded capability for supplying high pressure air to the model has recently been completed 

for the UPWT. As shown in figure 6, high pressure air at nearly 5,000 psi is controlled and fed 

to the model through a digital control valve (DCV). The DCV provides manual control of both 

temperature (by using an inline heater) and pressure over the ranges of ambient to 275°F and 50 

psi to 3,800 psi, respectively. The mass flow control range is 0.02 to 30 lbm/s at these 

conditions. Control accuracy is better than ±2 percent for the pressure range of 50–250 psi, ±1

percent for the pressure range of 250–3,800 psi, and ±5°F in temperature.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

7

Figure 6. Simplified schematic of the UPWT high pressure system.

2.2 Model 

The issues that affected the design of this model are discussed in detail in reference 19. A sketch 

of the final design is provided in figure 7. After refinement based on pretest computations, a 5 in 

diameter SRP model was selected. The model includes a highly instrumented 70 degree spherecone forebody with locations for four nozzle or plug inserts, followed by a 9.55 in long 

cylindrical aftbody. A cutaway sketch is provided in figure 8, showing that the assembled model 

was designed with a partially hollow sting that feeds an internal plenum connected to each 

nozzle location via a four-port manifold. The plenum is a constant diameter pipe with a 5 

degrees flare leading to the manifold. The predicted Mach number within the main plenum is on 

the order of 0.1 for worst-case conditions (highest mass flow rate). The sting and manifold 

assembly provides the structural load path to hold the forebody with either plugs or nozzles in 

place. The aftbody, comprised of two half-cylindrical shells, provides a non-load bearing 

enclosure intended to protect the internal instrumentation (also shown in figure 8). One 

nozzle/plug location is on the model centerline, while the other three are located at a radial 

distance midway between the centerline and maximum forebody radius and spaced 120 degrees 

apart. These locations can accommodate either a nozzle or a plug. The nozzles built for this 

study had a 4:1 exit-to-throat area ratio. The plugs provide a baseline forebody surface with no 

steps or gaps. The model was not designed to replicate any current configuration or full-scale 

system but rather to provide generic CFD validation data for a range of jet configurations and 

conditions. The design drawings for the as-built model are provided in Appendix A. 

Photographs of the individual components and partial assemblies obtained during the model 

acceptance fit-check review are also provided in Appendix A.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

8

Figure 7. Oblique view of UPWT SRP model assembly.

Figure 8. Major components of UPWT SRP model assembly.

One unique component of this model that warrants further discussion is the manifold assembly 

design and fabrication. The manifold encloses the main plenum and provides the ports to each 

individual nozzle. This part consists of a laser-sintered stainless steel front plenum (see DWG 

1168292 in Appendix A) and a Type–304 stainless steel nozzle interface plate (DWG 1168293) 

that together hold the inserts and forebody in place. These two components were brazed 

together, and this assembly was inspected and qualified prior to final machining (see DWG 

1168298). Once the manifold assembly was completed, a hydrostatic pressure vessel bench test 

was conducted to 3,750 psi (or 150 percent of the maximum planned pressure, 2,500 psi) prior to 

initiation of the wind tunnel test.

The use of heated high pressure air induced concern regarding the internal temperature of the 

model where the pressure instrumentation would reside (ref. 19. An insulating barrier was added 

to the model to reduce conduction heating of the instrumentation modules. For the insulating 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

9

barrier between the plenum/sting and the pressure modules, a tough, machinable thermoplastic 

material called ULTEM® 1000 was used. This high performance polymer maintains its high 

strength and rigidity even at elevated temperatures, thus providing an excellent platform with 

which to attach and isolate the modules. This piece is shown in light green of the cutaway of 

figure 8. This insulating barrier was sufficient to maintain the pressure instrumentation within 

acceptable temperatures during the test. Figure 9 provides an oblique view of the final design of 

the insulator saddle block showing the mounting holes for assembly. The saddle block provides 

attachment surfaces for three pressure modules.

Figure 9. Oblique view of insulator saddle block.

The model was also designed to minimize down time for configuration changes. The design 

included small, easily replaceable inserts for the nozzles and plugs. The use of inserts was 

preferable to reduce impact on planned surface pressure taps on the forebody. The pressure 

tubes were installed with slack to allow the swap-out of inserts with pressure tubing connections 

left intact, minimizing the number of leak checks during the test campaign. In addition, the 

pressure tubing was installed with quick disconnects, in case either the forebody or pressure 

modules needed removal for any reason. Configuration changes were initiated by removing the 

uninstrumented cylindrical shell, allowing access to the bolts that secure the forebody. Sliding 

the forebody forward a few inches on the long bolts provided enough clearance to remove and 

replace the inserts. Three out of four baseline plug inserts had built-in surface pressure taps (see 

DWG 1168294 & 1168295), which required additional tubes to be connected to the pressure 

modules. Two of the four nozzle inserts (one on centerline, also shown in figure 10, and one on 

the periphery) had internal high pressure and temperature instrumentation (for measuring 

pressure losses between the main plenum and the nozzle throats) that required connection to the 

data acquisition system.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

10

Figure 10. Close up of the instrumented center nozzle.

2.3 Instrumentation 

The primary measurements on the model was 167 surface pressure ports connected via 0.040

inch diameter flexible urethane tubing to three Pressure Systems, Inc. (currently owned by 

Measurement Specialties) electronically scanned pressure (ESP) transducer modules located 

within the model. Two 64-port modules (0–5  0.005 psid) were used to measure surface static 

pressures at 118 locations on the model forebody, as well as 4 locations on the aftbody, while a 

48-port (0–2.5  0.003 psid) module was used to measure pressures at the remaining 45 locations 

on the aftbody. A sketch of the surface port locations is provided in figure 11. Note that on the 

aftbody, all instrumentation was placed on the portside shell ( = 180° to 360°) to allow easier 

access to the internal compartment. A high number of pressure ports were desired to provide 

data for CFD validation and to aid posttest experimental uncertainty analysis. Table A-1

provides the locations for all surface pressure measurements. All three modules were teed to a 

common reference pressure that was pulled down to a hard vacuum to provide absolute pressure 

measurements. Three separate known pressures were supplied by Ruska Model 6211–801 

pressure gages (0–38  0.004 psia) to transducers on each ESP module and were monitored to 

check for drift in the ESP pressure measurements. In-situ ESP calibrations were performed

using the system Model 8432–15A pressure calibration unit (PCU, 0–15  0.003 psia) when the 

drift exceeded 2.5 psf.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

11

Figure 11. Forebody surface instrumentation layout for the baseline 

configuration.

Seven 0.0625-inch diameter Kulite XCS–062–5A pressure transducers (0–5  0.013 psia) were 

mounted flush to the surface of the model forebody, also shown in figure 11, with an adhesive 

potting material and used for measuring fluctuating surface pressures. The Kulites were included 

to monitor and measure any high frequency oscillations arising from the jet/free-stream 

interactions. Two additional Kulite transducers were mounted in the model aft shell just behind 

the shoulder but were unfortunately damaged during model assembly. The output signals from 

the Kulite gages were split to both the standard and high speed data acquisition systems to 

provide simultaneous time-averaged and unsteady pressure measurements.

Pressures were measured in the model at different locations along the high pressure airflow path 

using up to four Kulite XT–190–2000A pressure transducers (0–2000  2 psia). Two 

transducers were located at different stations in the model plenum (see figure 8), with the gages 

mounted flush to the inside surface of the plenum chamber. The remaining two pressure 

transducers were connected and used for measuring internal pressure losses between plenum and 

nozzle. These ports were located 0.417 inches upstream of the nozzles for both the center and a

periphery nozzle. Figure 10 provides a representative sketch of the center nozzle, showing the 

location of the pressure and temperature instrumentation just ahead of the nozzle. These 

transducers were active only when their respective nozzles were installed in the model. Plenum 

temperatures were measured using a 6 mm diameter Omega RTD–NPT–72–A platinum 

resistance temperature detector (RTD) probe (132–910  1°R) embedded 0.5 inches into the high

pressure airflow. Additionally, each of the two instrumented nozzles contained a Type K 

thermocouple (132–2,742  4°R) mounted flush to the inside surface and opposite of the plenum 

pressure port (shown in figure 10).

A NASA Langley built accelerometer was installed internal to the model (noted as Q-Flex in 

figure 8) and used to directly measure model pitch angle during the test. The device was 

calibrated in place as a function of pitch and roll angles using a multi-axis Langley Angle 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

12

Measurement System (AMS) (ref. 26) installed on the model during setup. The resultant 

calibration accuracy was approximately 0.01 degrees.

Eight Type K thermocouples (132–2,742  4°R) were installed to monitor and measure the 

thermal environment inside the model during the test. One thermocouple was mounted 

underneath each ESP module as well as the accelerometer, while the remaining four 

thermocouples were mounted to the inside surface of the aft shell at a location of approximately 

half the model length and every 90 degrees around the circumference.

A calibrated Flow–Dyne Engineering subsonic venturi flow meter with a 1.503 inch diameter 

inlet and 0.695 inch diameter throat was installed in the high pressure air line just outside of the 

test section and used to measure the mass flow rate of air exhausting through the model nozzles. 

The venturi inlet pressure was measured using a Druck PDCR 4060 pressure transducer (0–3,000 

 2.4 psia), while the inlet temperature was measured using a 0.25-inch diameter Type T 

shielded thermocouple probe (132–1,122  2 R). The pressure drop across the venturi throat was 

determined with a Bell & Howell Model 4–351–0004 differential pressure transducer (0–100 

0.05 psid) that was calibrated in one direction to increase accuracy.

To capture the dynamics of flowfield interactions between the bow and barrel shocks, a high 

speed digital camera was used to record the schlieren video. The Phantom 12, from Vision 

Research, is a 1 megapixel camera capable of taking more than 6,200 frames per second (fps) at 

full 1280 x 800 resolution and up to 1,000,000 fps at reduced resolution. For the present test, 

framing rates between 5,000 and 10,000 fps were used.

2.4 Test Conditions and Run Matrix

Table A-2 provides a complete list of parameters for this test. Table B-1 provides the notional 

run matrix and shows the key parameters of importance such as the configuration (number of 

nozzles), model attitude and location (angle of attack, roll, and position within the tunnel), 

free-stream conditions (Mach and Reynolds numbers), and nozzle conditions (thrust coefficient, 

and plenum pressure and temperature). The run matrix provides the pretest plan for sequencing 

the test in that it reflects the intended order for varying the key parameters. For instance, for any 

given configuration, an angle of attack sequence is obtained prior to changing the roll angle, strut 

position, plenum condition, or Mach number, in that order. To limit the scope of the present 

study, only a single low Reynolds number condition was considered for each Mach number of 

interest, as shown in figure 12. The lower Reynolds numbers allowed for the highest range of

thrust coefficients obtainable for the study, as thrust coefficients are inversely proportional to the 

tunnel dynamic pressure. To summarize, the tunnel test conditions for this study include Mach 

numbers of 2.4 and 3.5 at a Reynolds number of 1.0x106/ft, and 4.6 at a Reynolds number of 

1.5x106/ft; model positional settings for angles of attack of 0, ±4, ±8, 12, 16, and 20 degrees, roll 

angles of 0, 60, 120, and 180 degrees, model x positions of 25, 40, and 50 inches, and y positions 

of 0 and ±8 inches; and high pressure air conditions of pressures ranging from 0 to 1,500 psi and 

temperatures ranging from 120°F to 170°F.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

13

Figure 12. Test conditions within operating envelope for UPWT Test Section 2.

2.5 Data Acquisition & Reduction

The parameter list provided in Table A-2 also lists the equations used for data reduction for this 

test. The ESP surface pressure measurements were acquired with the Esterline 8400 System at 

10 samples/sec. Remaining data channels were acquired at 30 samples/sec through a NEFF 620 

signal conditioner/multiplexer system. The NEFF channels were processed through analog 1 Hz, 

low pass, four-pole Butterworth filters and recorded using a MODCOMP 88100 computer at 16

bit analog-to-digital (A/D) conversion. Both systems used a sampling period of 2.5 seconds. 

The unsteady pressure data from the Kulite transducers were sampled at 40,000 samples/sec for a 

2.5 second sampling period using a National Instruments/Labview-based high speed data system 

synchronized to the standard data system. These data were processed through a 20 kHz low pass 

filter and recorded at 16-bit A/D conversion.

Raw voltages from the instrumentation were recorded and processed in real time through 

respective calibration functions into engineering unit values for real-time display, monitoring, 

and plotting. Facility flow conditions were calculated via standard gas dynamic equations using 

measured tunnel stagnation conditions and calibrated values of free-stream Mach number. These 

flow conditions were then used to compute parameters such as the surface pressure coefficients, 

nozzle pressure ratios, nozzle exit-to-static pressure ratios, and nozzle thrust coefficients.

The measured plenum static pressures were corrected to total pressure values using total-to-static 

pressure ratios calculated from estimates of the plenum Mach number. These estimates were 

computed from a binomial approximation of the mass flow rate equation using the measured 

mass flow rates, plenum temperatures, and plenum cross section areas, and are valid for small 

values of Mach number. Nozzle exit conditions were calculated based on the plenum total 

conditions and the nozzle exit-to-throat area ratios. The thrust of each nozzle was computed 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

14

from the total measured mass flow rates and the ratio of the individual nozzle throat area to the 

total nozzle throat area.

The model nose position relative to the test section coordinate system was computed for each 

data point based on the axial and lateral movements of the model support system as well as the 

pitch and yaw angles of the model. Positional information was then used during the uncertainty 

assessment phase of the data analysis process. No attempt was made to correct the model angle 

of attack for noted flow angularity for this facility. Instead, any tunnel flow angularity was to be

captured as part of the uncertainty assessment (ref. 22).
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

15

 SECTION 3

TEST SET UP AND EXECUTION

Model installation into the tunnel began early in July 2010. Figure 13 provides a photograph of 

the model installed within the UPWT. A few days were required to install the model and high 

pressure air supply line, along with a careful installation and systematic leak checking of each 

pressure tube connection between the surface pressure ports and the ESP modules, (see figure 

14). In situ calibrations of the ESP modules and the air supply venturi were also conducted using 

the facility as a vacuum chamber prior to the start of the test in order to insure systems were 

behaving as expected.

Figure 13. The SRP model installed in the UPWT Test Section 2.

Figure 14. The internal pressure lines and instrumentation wiring.

The test team held a prioritization meeting the week preceding test initiation to revise the run

matrix, allowing for lower priority objectives to be omitted if testing appeared behind schedule. 

The matrix was updated to include a three tiered priority system: 1 being the highest priority, 2 

being cases that should be obtained, time permitting, and 3 being cases only considered if ahead 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

16

of schedule. Table B-1 provides the run matrix as laid out by the pretest prioritization meeting 

with the sequence of parametric variation from first to last; however, the actual run numbers 

obtained for each case replace the prioritization numbers that would have been listed in the three 

right-most columns. In the cases where a lower priority item was dropped from the test, the table 

cell is left blank with a gray filler. Table B-2 provides corresponding plenum conditions for 

nominal thrust coefficients that were planned for during the test. The actual run-averaged tunnel 

and nozzle flow conditions obtained for each run are provided in the run log listed in Table B-3. 

The angle of attack pitch pause schedule for each run is provided in Table B-4. Statistical 

analyses of all test points obtained for a given flow condition are provided in Table B-5. 

Schlieren video data was not acquired for every run and angle of attack because of file memory 

and transfer constraints. Table C-1 provides a summary of the schlieren video data obtained 

during the test.

The model provided for four configurations: (1) the baseline model, with plug inserts in all four 

locations, (2) the center nozzle, with plug inserts in the three peripheral locations, (3) the trinozzle, with a plug insert in only the center location, and (4) the quad-nozzle, with no plug 

inserts. The first three configurations were considered Priority 1, while the quad configuration 

was considered Priority 2. In the end, all four configurations were tested. For the angle of attack 

sweep, the tunnel pitch mechanism was programmed to pause at –8, –4, 0, 4, 8, 12, 16, and 20 

degrees and a repeat of 0 degrees, in that order. This sweep sequence was used for most of the 

test. (There were a few cases at the highest angle of attack and thrust coefficients in which the 

tunnel seemed close to tunnel unstart, so these cases were omitted.) To extend the spatial 

coverage of the clustered instrumentation, model roll angles of 0, 60, 120, and 180 degrees were 

used. Model roll also provided repeatability data with select angle of attack cases (e.g.,  = –4 

degrees with 0 degree roll is a repeat of  = 4 degrees with 180 degrees roll). A full range of 

streamwise (X) and lateral (Y) model translations were considered important for the uncertainty 

estimation, especially for the baseline configuration, to provide repeatability data from different 

stations within the tunnel. For the baseline configuration, independent translations in either the X

or Y directions were considered Priority 1 and combined X and Y translations were considered 

Priority 2. For the nozzle configurations, only X translations were considered as Priority 2, while

X and Y translations were considered Priority 3. When nozzles were installed in the model, the 

plenum pressure was controlled and adjusted via the DCV, with a fixed temperature near 170°F 

to provide the thrust coefficients listed in Table B-2. A broad range of thrust coefficients was 

considered Priority 1, although additional cases were captured as part of the pretest matrix as 

Priority 2. For tunnel operating conditions, the widest possible range of Mach numbers for Test 

Section 2 at a single unit Reynolds number case was considered a top priority. Mach numbers of 

2.4 and 3.5 at a Reynolds number of 1.0x106/ft, and 4.6 at a Reynolds number of 1.5x106/ft were 

used. To reduce likelihood for tunnel unstarts, these conditions were selected to be a safe margin 

above the lower limit of the operating envelope of the tunnel, as shown in figure 12.

The baseline configuration is shown in figure 15, which also shows some of the port side 

instrumentation bundles strapped to the outside of the tunnel hardware. In this photo, the model 

has been rolled to the 180 degrees position such that the air supply feed line is at the bottom. 

Figure 16 provides a sequence of starboard side photos showing the location of the 

instrumentation and high pressure lines for each roll increment of zero (with the air supply line 

on top) to 180 degrees. The baseline runs were primarily intended for quantifying various 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

17

sources of experimental uncertainty. The lateral and streamwise translations to various stations 

within the tunnel coupled with the model rolls allows for sensor-to-senor comparisons such that 

instrumentation and flowfield uniformity uncertainties can be estimated. In the streamwise 

direction, the model translations are notionally 15 in forward and 10 in back. In the lateral 

direction, the model translations are ±8 in. 

Figure 15. The baseline model installed in Test Section 2.

(a) Roll = 0 degrees. (b) Roll = 60 degrees.

(c) Roll = 120 degrees. (d) Roll = 180 degrees.

Figure 16. The baseline model installed in the UPWT.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

18

Figure 17 provides another starboard side photo of the center nozzle configuration showing the 

downstream attachment points for the instrumentation bundle and air supply line. The center 

configuration represents the simplest nozzle case for CFD comparisons and the data most similar

to historical results. In reference to the run matrix shown in Table B-1, a few streamwise 

translation cases were planned but not performed because of time constraints. In addition, many 

of the 60 and 120 degrees roll cases were omitted also because of time constraints, as they were 

considered redundant for this axisymmetric case. 

Figure 17. The center nozzle configuration installed in the UPWT.

The tri-nozzle configuration, shown in figure 18, was also deemed important for comparison 

against historical data, as there have been previous studies that looked at multiple nozzles located 

towards the model periphery. The location of these nozzles, at the midpoint of the radius of the 

forebody, is unique, however, closer inboard than all previous studies. During the test, most 

Priority 1 cases were acquired with the exception of the highest thrust coefficient and late repeat 

cases. Priority 2 and 3 cases planned to acquire model translation data on the tri nozzle were not 

acquired due to time constraints.

Figure 18. The tri-nozzle configuration installed in the UPWT.

The quad-nozzle configuration was originally Priority 2; however, a real-time team decision was 

made during the test that this data would be unique due to the addition of the center nozzle, 

which had not been studied before. Due to time constraints, the range of thrust coefficients 

acquired for the quad configuration was reduced to only a few cases. 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

19

 SECTION 4

DISCUSSION OF RESULTS

The following figures and discussion provide a review of key observations from the test. These 

figures include schlieren still frame images (extracted from the high speed videos) and 

corresponding forebody surface pressure coefficient data (line plots and contour maps) to 

illustrate trends. The schlieren images used within figures included in this section have been 

zoomed and cropped to enlarge the details of interest. The original full frame images can be 

found within the schlieren appendix. Note that in the pressure data line plots to follow, polar 

coordinates are used for axisymmetric data ( = 0°) with a ray emanating from the model 

centerline, and Cartesian coordinates are used for nonaxisymmetric data ( ≠ 0°) with a ray of 

data across the width of the model. For completeness, all results are contained within appendices 

in run chronological order: schlieren images, including representative still frames and time 

averaged and standard deviation results, in Appendix C surface pressure data in line plot format 

for select rays on the forebody and aftbody in Appendix D; and forebody contour maps derived 

from the pressure data in Appendix E. The high frequency data analysis and uncertainty 

assessment are to be published separately, although preliminary results have been published in 

references 21 and 22, respectively. In the discussion to follow, observations of unsteadiness are 

qualitatively assigned based on a review of the video data. In these cases, the “unsteadiness” can 

be seen through bow shocks and/or plumes that appear irregular in shape in the still frame 

images, or blurry in the time averaged images captured in the appendix.

4.1 Baseline

Figure 19 provides the effect of Mach number for the baseline configuration at  = 0°. As 

expected, the bow shock moves closer to the forebody, and the pressure coefficient increases as 

the Mach number increases. Note that the distance between the slats in the schlieren window is 

5.5 in, with each slat measuring 1.25 in. These can be used as scales to roughly estimate bow 

shock location as a function of Mach number, with the standoff distance decreasing by an 

approximate factor of two when going from Mach 2.4 to 4.6. The stagnation pressure coefficient 

increases by roughly 5 percent between Mach 2.4 and 3.5, but less than 1 percent going to Mach 

4.6. The smaller increase in pressure between the two highest Mach numbers is indicative of 

Mach number independence, as the stagnation point pressure coefficient asymptotes to a value 

near 1.8 as Mach number increases. 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

20

(a) Schlieren.

(b) Surface pressure.

Figure 19. The effect of Mach number for the baseline configuration at  = 0°.

Figure 20 provides the effect of angle of attack for the baseline configuration at M∞ = 4.6. 

These results are representative of all three Mach numbers. The flowfield is very steady for all 

angles of attack (see Appendix C). The pressure data, shown for a ray from top to bottom for 

this orientation, shows the stagnation point peak moving off the center nose radius onto the 

flatter cone region for the higher angles of attack. Also note in the schlieren images that the 

model translates downstream with increasing angle of attack due to the design of the model pitch 

mechanism.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

21

(a) Schlieren.

(b) Surface pressure.

Figure 20. The effect of angle of attack for the baseline configuration at M∞ =

4.6 (Run 283).

Figure 21 provides forebody pressure coefficient contour maps for the range of angles of attack 

at Mach 2.4 showing the global movement of the surface pressure for each test point. These 

global maps were interpolated from the pointwise measurements, as represented by the black 

dots for each sensor. All faulty sensors were omitted from the data file prior to the generation of 

the contour maps. It should be noted that these images are based on a body-fixed coordinate 

system. For the case shown here, Run 274, the model was rolled to φ =180° so that an upward 

pitch movement (i.e.,  = 20°) corresponds to decreased pressure on the lower half. These trends 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

22

are representative of the effect of angle of attack on the baseline configuration for all Mach 

numbers. All contour maps are contained within Appendix E along with a description of how 

they were generated.

Figure 21. Contour maps showing the effect of angle of attack for the baseline 

configuration at M∞ = 2.4 (Run 274).

4.2 Center Nozzle

The effect of Mach number for the center nozzle configuration at  = 0° and CT = 2 is shown in 

figure 22. The flow emanating from the center nozzle forms a barrel shock that is even wider 

(for these conditions) at the jet terminus (or triple point) than the model. The curved jet 

terminus, or Mach termination disk, is partially obscured by the window slats for this model 

location. However, there are other model positions contained in Appendix C that provide a 

better view of this region. Aside from the increased bow shock standoff distance due to the 

plume, the bow shock shapes are quite similar to those shown for the baseline configuration. 

The nozzle flow does induce a small amount of flow unsteadiness, in the annular triple point 

region, as can be seen by reviewing the standard deviation images of Appendix C. Aside from 

the slight triple-point “flapping,” the rest of the flowfield is quite steady for all Mach numbers at 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

23

 = 0°. The pressure data on the forebody, shown for a ray from the centerline to the shoulder 

are relatively flat, indicative of a large flow separation zone due to the annular recirculation of 

the nozzle plume. Note that the pressure taps from r/R of 0 to 0.2 are located on the center plug, 

which is not installed for this configuration.

(a) Schlieren.

(b) Surface pressure.

Figure 22. The effect of Mach number for the center nozzle at  = 0° and CT = 2.

The effect of increasing thrust coefficient for the center nozzle at M∞ = 4.6 and  = 0° is shown 

in figure 23. The bow shock standoff, as well as the maximum width of the barrel shock, is 

directly affected by the thrust coefficient. Note that, for the images of figure 19 and figure 23, 

the model is in the same location, nearly aligned with the third window slat from the right. For 

the lowest thrust coefficient (CT = 0.5), the bow shock stand off distance is significantly 

increased from just in front of slat #3 for the baseline case (shown in figure 19) to almost 

touching slat #4 (the distance between the slats is roughly 5.5 in). Further increase of the thrust 

to CT = 3.0 resulted in further increase of the stand off distance (now ahead of slat #4). 

Extraction of the standoff distances will be further examined and discussed at the end of this 

section. The video data (see Appendix C) reveals, as with the previous example, that the 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

24

flowfield is steady, with the exception of the triple point region, for the range of thrust cases 

acquired. The pressure data suggests that the forebody is mostly separated, with the shoulder 

region being most affected by the changing thrust levels. The pressure coefficient at the shoulder 

drops from 1.48 for the baseline no blowing result (shown previously) to roughly 0.29 at CT = 

0.5 and then down to just below zero at CT = 3.0. 

(a) Schlieren.

(b) Surface pressure.

Figure 23. The effect of thrust coefficient for the center nozzle at M∞ = 4.6 and 

 = 0°.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

25

The contour maps can also be used to visualize the global effect of the increasing thrust or plume 

size. Figure 24 provides a comparison of the contour maps to the corresponding schlieren 

images for a range of thrust cases at Mach 2.4 and  = 0°. For the higher thrust cases, the size of 

the Mach disk at the end of the plume is greater than the forebody diameter, effectively shielding 

the forebody from the oncoming flow. For thrust coefficients less than or equal to one, the 

plume only partially shields the forebody, thus the shoulder region sees an increase in pressure as 

a result. At the lowest thrust case, the schlieren image suggests a new compression shock ahead 

of the forebody shoulder, indicating supersonic flow in that region. The trends shown here for 

Mach 2.4 are representative of those observed for other Mach numbers.

Figure 24. Comparison of contour maps to Schlieren for a range of thrust 

cases for the center nozzle configuration at M∞ = 2.4 and  = 0° 

(Runs 319, 139, 141, 137, and 136, respectively).

Figure 25 provides the effect of angle of attack for the center nozzle configuration at  = 4.6 

and CT = 2. As mentioned earlier, irregular bow shocks and plumes can be used as a gross 

indicator of unsteadiness and this is evident in the image shown for the highest angle of attack. 

However, at moderate angles of attack the observed unsteadiness is more localized to the 

windward triple point region and thus the still frame image shown for  = 12° does not appear 

irregular, although a slight bulge in the bow shock is seen. Thus, the jet interaction region 

flowfield becomes increasingly unsteady for the center nozzle at angles of attack greater than 10 

degrees, first emanating in the triple point region and then encompassing the entire flowfield. 

Appendix C provides additional processing that allows assessment of the unsteadiness observed 

from the schlieren video. The forebody pressure data, shown for a ray from top to bottom for 

this orientation, indicate that the windward surface pressure increases while the leeward 

decreases as the angle of attack is increased. The trends shown here for  = 4.6 and CT = 2 are 

fairly typical of those observed with the other Mach and thrust cases.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

26

(a) Schlieren.

(b) Surface pressure.

Figure 25. The effect of angle of attack for the center nozzle at M∞ = 4.6 and 

CT = 2 (Run 165).

Figure 26 provides the forebody pressure contour maps for the complete range of angles of 

attack obtained during Run 141, which is for the center nozzle configuration at Mach 2.4 with a 

thrust coefficient of two and a roll angle of zero. Elevated pressures are evident on the windward 

side of the forebody (the lower portion for positive angles of attack), specifically on the forebody 

shoulder and a small region nearer to the nozzle, perhaps due to a horseshoe vortex. The results 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

27

shown here are fairly typical of the other Mach and thrust cases for the center nozzle, with the 

exception of the highest thrust case (Run 136). For Run 136, at Mach 2.4 and CT = 4, the bow 

shock could be seen to be interacting with the tunnel sidewalls (the downstream bow shock 

“shadow” seen most clearly in the standard deviation images, the right-most column in Appendix 

C) for all angles of attack. When the model was pitched up to 12 degrees during Run 136, the 

flow became highly unsteady in contrast to the lower thrust cases, and the higher angle of attack 

cases were dropped from the run. The corresponding contour maps (see Appendix E) for this run 

reveal an asymmetric pattern that also suggests the possibility of a tunnel interference effect.

Figure 26. Contour maps showing the effect of angle of attack for the center 

nozzle configuration at M∞ = 2.4 and CT = 2.0, and φ = 0° (Run 141).

The schlieren data were used to extract the dimensions of relevant flow features for the center 

nozzle case, specifically the shock stand off distance and radius, and the jet plume length and 

radius, as shown in figure 27. These dimensions are intended as scaling parameters to assist in 

the development of engineering relations for predicting SRP thrust behavior. The extraction was 

performed from scaled tracings of the steady state flow features using Adobe Illustrator. First 

the schlieren images, including the still, average intensity, and standard deviation images 

captured in Appendix C, were imported onto different layers within Illustrator and aligned to 

overlay each other. Then, on a fourth layer, the relevant features were traced to fit all three 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

28

sources of information. Each “data” layer could be made visible or invisible as needed to 

compare the tracing to all three images. In certain cases, when a flow feature was hidden behind 

one of the window slats, an alternate run, where the model was physically moved to a different 

location within the tunnel, was used to assure that the tracing was correctly captured. For all 

cases, the schlieren images were aligned with the model as the reference point. This process was 

completed for the range of thrust cases for each Mach number, and also one angle of attack 

sweep. The model width (diameter of 5 inches) was then used to scale the entire ensemble of 

tracings, and the feature lengths and radii were extracted. 

Figure 27. Relevant dimensions to be extracted from the Schlieren data.

The center nozzle shock and plume tracings are shown in figure 28 for all three Mach numbers at 

 = 0°, each for the acquired range of thrust coefficients. The extracted dimensions, as well as 

corresponding pressure and mass flow ratios for each run, are listed in Table 1. The ratios 

chosen to reflect the nozzle performance for each run are the ratio of jet static exit pressure to 

free-stream, post shock total pressure (PJ/PT2) and jet mass flow rate to tunnel mass flow rate 

(mJ/m∞) ratios.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

29

(a) Bow shock and plume shapes as a function of CT for Mach 2.4.

(b) Bow shock and plume shapes as a function of CT for Mach 3.5.

Figure 28. Center nozzle shock and plume tracings for all three Mach numbers 

at  = 0°.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

30

(c) Bow shock and plume shapes as a function of CT for Mach 4.6.

Figure 28. Concluded.

Table 1. Extracted flow features and properties for the center nozzle for  = 0°.

M∞ CT Test/Run PJ/PT2 mJ/m∞ LS

(in) RS (in) LJ (in) RJ(in)

2.4

0 T1853/274 – – 1.04 3.92 – –

0.46 319 1.9 0.0017 4.18 6.61 2.59 1.06

0.97 139 3.8 0.0036 5.63 8.81 3.66 1.64

1.98 141,318 7.5 0.0074 7.54 11.79 4.99 2.59

3.00 137 11.2 0.0113 9.10 14.10 5.69 3.37

4.02 136 14.7 0.0150 10.47 16.31 6.81 4.10

3.5

0 T1853/276 – – 0.71 2.97 – –

0.22 158 1.0 0.0009 3.14 4.21 1.99 0.56

0.45 157 2.0 0.0020 3.98 5.44 2.59 1.06

0.94 154 4.0 0.0042 5.35 7.21 3.67 1.77

1.97 153,320 7.8 0.0087 7.24 9.83 5.09 2.95

2.96 150 11.7 0.0132 8.86 12.40 5.78 3.70

4.6

0 T1853/86 – – 0.68 2.93 – –

0.22 171 1.0 0.0011 3.10 3.98 2.07 0.64

0.45 169 2.0 0.0022 3.91 5.22 2.62 1.17

0.94 167 4.0 0.0047 5.34 6.97 3.70 1.95

1.97 165,321 8.0 0.0095 7.22 9.67 5.09 3.04

2.96 163 11.8 0.0145 8.58 11.52 5.78 3.75
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

31

From the tabulated data, one can surmise that the plume shape is primarily driven by the ratio of 

the jet static pressure to the post shock total pressure, as the plume dimensions are largely 

consistent between the three Mach numbers. On the other hand, the shock standoff distance 

varies with Mach number. An effective body, which represents the fluid boundary between the 

two flowfields (the jet plume on the model side and the free stream on the other) is of interest, 

but is not easily seen in the schlieren imagery. The difference between the shock standoff 

distance for the blowing and nonblowing cases (LS – LS0) can be used as an estimate of the 

effective body length. Doing this also shows a direct relation between the effective body and the 

jet pressure ratio (PJ/PT2), regardless of Mach number. The dependence of the standoff distances 

(referenced to the nozzle exit diameter) to the jet pressure ratio are shown in figure 29. Note that 

the jet plume and effective body standoffs are largely independent of Mach number.

Figure 29. Flow feature stand off distance versus nozzle pressure ratio for 

 = 0°.

The effect of angle of attack was looked at for the center nozzle at Mach 4.6 and CT = 2, 

including comparison of repeat runs. The angle of attack tracing results are shown in figure 30. 

With the model as the point of reference and CT held constant, the plume shape can be seen to be 

fairly invariant to angle of attack. The bow shock pivots around the plume as angle of attack 

changes. For cases where blunt, stable plumes are established, the bow shock and plume regions 

behave independently with the effective body as the interface boundary.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

32

Figure 30. Bow shock and plume shapes as a function of  for Mach 4.6, CT = 2.

4.3 Tri-Nozzle

Figure 31 provides the effect of Mach number for the tri-nozzle configuration at  = 0° and 

CT = 2. As shown by the irregular shape captured in these single frame images, the bow shocks 

are unsteady, making it more difficult to accurately estimate stand off distances. In general, the 

tri-nozzle was the least steady configuration of the four tested across the spectrum of Mach, 

thrust, and angle of attack cases acquired during this test. The pressure data on the forebody, 

shown for a ray from the centerline to the shoulder, is relatively flat for  = 2.4, indicative of a 

large flow separation zone due to recirculation around the periphery of the nozzle jets, while the 

higher Mach numbers show increased pressure in the center plug region. Note the pressure taps 

from r/R of 0.4 to 0.6 are located on the peripheral plug, which is removed for this configuration.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

33

(a) Schlieren.

(b) Surface pressure.

Figure 31. The effect of Mach number for the tri-nozzle at  = 0° and CT = 2.

The effect of increasing thrust coefficient is shown in figure 32 for the tri-nozzle configuration at 

M∞ = 4.6 and  = 0°. At the lowest thrust coefficient (CT = 0.5), the jet plumes independently 

protrude through the bow shock and are unsteady. As shown, this lower thrust case also 

corresponds with the higher measured forebody pressures. This particular case is likely an 

example of the unstable long penetration mode discussed earlier. As thrust is increased, the 

individual jets broaden and coalesce, forcing the bow shock further away from the forebody and 

lowering the measured surface pressure. The bow shock structure for these higher thrusting 

cases is mostly steady with periodic perturbations emanating from a region in front of the three 

jets (see Appendix C), although the level of unsteadiness appears to increase slightly for the 

highest thrust cases acquired.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

34

(a) Schlieren.

(b) Surface pressure.

Figure 32. The effect of thrust coefficient for the tri-nozzle at M∞ = 4.6 and  = 0°.

Figure 33 provides a comparison of the contour maps to the corresponding schlieren images for a 

range of thrust cases at Mach 2.4 and  = 0°. For the higher thrust cases, the size of the merged 

Mach disks at the end of the plumes is greater than the model diameter, effectively shielding the 

forebody from the oncoming flow. For a thrust coefficient of one, the plumes appear blunt, 

displacing the bow shock globally, but are not totally merged as some aerodynamic pressure is 

seen in the boundaries between the three nozzles. For thrust coefficients less than one, the 

plumes are completely independent, thus, exposing the forebody to a significant increase in 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

35

aerodynamic pressure. For the two lowest thrust cases, the schlieren images show the plumes 

protruding through the bow shock and from the videos one can see the protrusions as highly 

dynamic. Figure 34 provides just the contour maps for the entire range of thrust cases for the trinozzle at Mach 2.4 and  = 0°. The trends shown here for Mach 2.4 are representative of those 

observed for the other two Mach numbers.

Figure 33. Comparison of contour maps to schlieren images for a range of 

thrust cases for tri-nozzle configuration at M∞ = 2.4 and  = 0° (Runs 

180, 221, 202, 198, 194, and 190, respectively).

Figure 34. Comparison of contour maps for complete range of thrust cases for 

tri-nozzle configuration at M∞ = 2.4 and  = 0° (Run 179).
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

36

Figure 35 provides the effect of angle of attack for the tri-nozzle configuration at M∞ = 4.6, φ = 

180° and CT = 2. For the thrust case shown, the effect of increasing angle of attack serves to 

increase the overall level of unsteadiness. This observation holds true for both model 

orientations of φ = 0° and 180° at this thrust level (see schlieren for Runs 247 and 248, pages 180 

and 182). However, at higher thrust coefficients, model orientation plays a role in whether the 

flowfield is steady or not when the model is at angle of attack. For instance, at CT = 3, when the 

model is rolled to φ = 180° the flowfield becomes steady as angle of attack increases, while at φ

= 0° the flowfield remains unsteady. To see this in the schlieren results, please compare Runs 

262 and 263 in Appendix C (pages 186 and 187). This mode switching behavior was also seen 

with the quad nozzle configuration and thus will be discussed further in the next section. In 

terms of the pressure data trends, shown for a ray from top to bottom with the peripheral plug 

centered on the windward side (φ = 180°), CP increases on the windward ray with increasing 

angle of attack, while the centerline and leeward regions decrease. 

(a) Schlieren.

Figure 35. The effect of angle of attack for the tri-nozzle at M∞ = 4.6 and CT = 2 

(Run 248).
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

37

(b) Surface pressure.

Figure 35. Concluded

Figure 36 provides comparison of forebody CP contours for the range of angles of attack and roll 

at Mach 2.4 and CT = 1. For angles of attack of 16 degrees and higher, the orientation of the 

nozzles significantly affect the forebody flow, with the φ = 0° and 120° cases displaying the 

highest pressures. For these two cases, the windward side of the model has two nozzles on either 

side of centerline, allowing a high pressure region to form between the nozzles at high angles of 

attack. The other cases (φ = 60° and 180°) have just one nozzle bisecting the windward 

centerline, effectively diverting high pressure from the surface. The trends shown here for Mach 

2.4 are representative of those observed for the other two Mach numbers.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

38

Figure 36. Comparison of contour maps for a range of angle of attack and roll 

cases for the tri-nozzle configuration at M∞ = 4.6 and CT = 2.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

39

Shock and plume tracings were also investigated for the multi nozzle cases, but the increased 

level of flowfield unsteadiness resulted in more subjective extraction of relevant dimensions. An 

example is provided in figure 37, which was completed for the tri nozzle configuration at Mach 

3.5 and  = 0° providing shock and plume tracings for the range of acquired thrust coefficients. 

When possible, multiple cases were used to establish qualitative repeatability within a given 

thrust level. It is interesting to note that at the higher thrust coefficients, repeatability appears to 

be fairly good, likely an indication of the relatively stable and steady bow shock behavior. At CT

of 3 and below, the bow shocks and plumes were noticeably less steady, which is reflected in 

less repeatable tracings. Due to the subjective nature of the results obtained for this case, 

tracings were not attempted for the rest of the multi nozzle configurations and cases.

Figure 37. Tri nozzle shock and plume tracings for M∞ = 3.5 at  = 0.

A comparison of the bow shock standoffs for the center and tri nozzle results at comparable 

thrust levels for Mach 3.5 and  = 0° is provided in figure 38, with the center nozzle shown by 

solid lines and the tri nozzle by dashed. As is illustrated in this figure, at equivalent thrust 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

40

coefficients, the center nozzle provides a greater displacement of the shock standoff distance 

than the tri nozzle. Also included are the corresponding jet pressure ratios for each case. Note, 

the 3 to 1 ratio in the difference in number of nozzles results in identical jet pressure ratios 

between the center nozzle with a CT = 1 and a tri nozzle with CT = 3. In the figure, this 

comparison is almost accommodated when comparing Run 154 for the center nozzle to Run 222 

for the tri nozzle. Thus, jet pressure ratio appears to be a better indicator of bow shock 

displacement, although for equivalent PJ/PT2 the tri nozzle does provide for a wider bow shock 

than the center nozzle.

Figure 38. Comparison of center and tri nozzle bow shocks for M∞ = 3.5 at  = 0.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

41

4.4 Quad-nozzle

The effect of Mach number on the quad-nozzle configuration at  = 0° and CT = 2 is provided in 

figure 39. A general observation is that the extra nozzle on center tended to reduce the level of 

flowfield unsteadiness, when compared against the tri nozzle results, for the limited set of 

conditions studied here. Even so, the bow shock is somewhat unsteady at the highest Mach 

number (as indicated by the irregular bow shock in the M∞ = 4.6 image). The pressure data on 

the forebody, shown for a ray from bottom to top, is relatively flat, indicating a largely separated 

forebody, with the pressure coefficient level rising with increasing Mach number. Note the 

pressure taps from –0.2 to 0.2 and 0.4 to 0.6 are not installed for this configuration.

(a) Schlieren.

(b) Surface pressure.

Figure 39. The effect of Mach number for the quad-nozzle at  = 0° and CT = 2.

The effect of increasing thrust coefficient is shown in figure 40 for the quad-nozzle configuration

at M∞ = 2.4 and  = 0°. Because of time constraints, only a limited set of thrust coefficients 

was acquired for the quad configuration. The Mach 2.4 case provides the widest range of CT and 

thus is shown here. For an angle of attack of zero, the bow shock is generally steady over this 

thrust coefficient range, with only minor and infrequent perturbations observed in the video, 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

42

although the frequency of these perturbations do increase as Mach and thrust increases (as seen 

in Appendix C). As shown with the pressure plot, the initial effect of increasing thrust is to lower 

the measured forebody pressures. However, once a CT = 2 is reached, there appears to be no 

further influence of thrusting on the measured pressure. 

(a) Schlieren.

(b) Surface pressure.

Figure 40. The effect of thrust coefficient for the quad-nozzle at M∞ = 2.4 and 

 = 0°.

An interesting feature was observed for the higher thrust cases on the quad nozzle configuration 

in the region of the virtual stagnation point, which was not seen previously with the tri nozzle. 

This feature, best described as a tripod with legs splayed out towards the bow shock, was 

revealed after rolling the model in 30 degree increments, see figure 40 as an example for the 

quad nozzle at M∞ = 2.4,  = 0°, and CT = 3. In these close-up comparisons of the plume region 

for the quad nozzle model rolled at φ = 0° and 30°, the “tripod” is more easily seen in the 

averaged intensity and standard deviation images for the φ = 30° case. At thrust levels sufficient 

to constrain and constrict the center plume, pressure relief is only allowed in a forward direction 

at each of the three interface boundaries between center and peripheral plumes (approximately 

the midpoint between any two peripheral nozzles).
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

43

Figure 41. The effect of model roll for the quad-nozzle at M∞ = 2.4,  = 0°, and 

CT = 3.

Figure 42 provides the angle of attack effect for the quad-nozzle configuration. In general terms, 

the quad-nozzle was steadier for similar angles of attack and thrust coefficients than the trinozzle. As mentioned earlier with the tri nozzle results, the quad nozzle configuration also 

showed that while at angle of attack, the orientation of the nozzles is important for establishing 

the dynamics of the flowfield. For example, figure 42 provides the sweep of angles of attack for 

the case where two of the peripheral nozzles are opposed on either side of the model windward 

symmetry plane (φ = 0°). In this orientation, the nozzle/bow shock interaction region is fairly 

unstable and unsteady at angles of attack of 16 degrees and higher. When the model orientation 

is such that one nozzle is located on the windward symmetry plane, such as is shown in figure 43

(φ = 180°), the flowfield for these high angle of attack cases becomes very stable and steady (see 

also Appendix C). From the pressure data comparison, the unsteady case corresponds to a 

greater increase in forebody pressure at the higher angles of attack than the steady case. In the 

case on the steady orientation, the windward jet serves to dominate the forebody pressure field 

through the separations surrounding the jet. 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

44

(a) Schlieren.

(b) Surface pressure.

Figure 42. The effect of angle of attack for the quad-nozzle at M∞ = 2.4, φ = 0°, 

and CT = 2 (Run 288).
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

45

(a) Schlieren.

(b) Surface pressure.

Figure 43. The effect of angle of attack for the quad-nozzle at M∞ = 2.4, φ = 180°, 

and CT = 2 (Run 291).
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

46

Figure 44 provides contour maps for the same range of angle of attack and roll cases as discussed 

previously, except at Mach 2.4 and CT = 1. For angles of attack of 16 degrees and higher, the 

orientation of the nozzles have a significant effect on the forebody flow, with the φ = 0° and 120° 

cases displaying the highest pressures. For these cases, the windward side of the model has two 

nozzles on either side of centerline, allowing a high pressure region to form between at high 

angles of attack. The other cases (φ = 60° and 180°) have the single nozzle bisecting the 

windward centerline, effectively diverting high pressure from the surface. The trends shown 

here for Mach 2.4 are representative of those observed for other Mach numbers.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

47

Figure 44. Comparison of contour maps for a range of angle of attack and roll 

cases for the quad-nozzle configuration at M∞ = 2.4 and CT = 1.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

48

4.5 High Frequency Analysis

While the high frequency sensors were an important element to this test, the magnitude of the 

dataset and analysis requires that these results be documented separately and by a different set of 

authors (ref. 27). Besides, from the context of the observations and conclusions reached within 

the present document, the high frequency results are ancillary. Quantitative observations 

of dynamic behavior will be most useful when compared against computational results, as was 

done in refs 28 and 29 based on the preliminary analysis of reference 21. From those published 

results, which only cover a subset of the Mach 4.6 data, the following observations were reached:

(a) in the absence of retrorocket flow, no detectable periodic dynamics were observed on the 

forebody; (b) once plume flow was established, different dynamics were observed depending on 

the thrust levels; (c) angle of attack did not strongly affect the dynamics observed, only 

modifying the peak frequency slightly; (d) for the center nozzle configuration, a strong peak 

frequency was observed at roughly 2kHz (with harmonics) for the CT = 2 case, which is 

consistent with published computational predictions (ref. 28); and (d) for the multi nozzle 

configurations, the measured frequency peaks become less distinct, an indication of the flow 

being less periodic (or more chaotic) in nature.

4.6 Uncertainty Analysis

A goal of this CFD validation experiment was to estimate the pressure coefficient uncertainties 

of the experimental data in order to provide a basis for comparison to CFD predictions. Data 

from the baseline non-thrusting model configuration were used to estimate separate components 

of uncertainty due to random error, flowfield nonuniformity, and model/instrumentation 

asymmetries over the full range of model angle of attack, roll angle, and test section axial and 

lateral locations. The components of uncertainty were estimated from the statistical analysis of 

residuals determined through the comparisons of measurements from certain parings of runs and

pressure ports. For instance, a comparison of replicate runs at the same Mach number, test 

section location, and model angular orientation yields information about the random error 

component of uncertainty. Conversely, a comparison of runs at the same model orientation but 

different locations in the test section provides information about uncertainty due to flowfield 

nonuniformity. Similarly, a comparison of different pressure port measurements for the same 

location in the test section, and the same location in the blunt body flowfield, would provide 

information about uncertainty due to model geometry/instrumentation asymmetries. The test 

matrix given in Table B-1 was used to identify pairs of runs from which the residuals were 

calculated for each of the three components of uncertainties discussed above.

A summary of the pressure coefficient uncertainties at one standard deviation is given in Table 2. 

For each Mach number, the uncertainties are broken out into the individual components along 

with a total uncertainty computed as the root-sum-square of the component uncertainties. The 

table also provides information about the number of data records and residuals that were used in 

the calculation of each component uncertainty, as well as the percentage contribution to the total 

variance for each uncertainty component. As the table clearly illustrates, the flowfield 

nonuniformity contributes most significantly to the overall uncertainty, a finding in qualitative 

agreement with that from other experiments reported in the literature and using the same analysis 

methodology. A complete discussion of the details of the uncertainty analysis and results will be
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

49

provided in a separate report (ref. 30); however, preliminary results were previously published in 

reference 22.

Table 2. Summary of the pressure coefficient uncertainties at one standard 

deviation.

Mach Uncertainty 

Source # Records, L # Residuals, N s

% Total 

Variance

2.4

Random 210 31,544 0.00111 8

Flowfield 830 126,108 0.00341 75

Geometry 786 60,990 0.00160 17

Total 1826 218,642 0.00394 100

3.5

Random 75 11,087 0.00183 10

Flowfield 780 118,332 0.00531 80

Geometry 528 37,720 0.00190 10

Total 1383 167,139 0.00593 100

4.6

Random 68 10,016 0.00294 15

Flowfield 410 62,010 0.00637 71

Geometry 320 28,392 0.00276 13

Total 798 100,418 0.00754 100
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

50

 SECTION 5

SUMMARY

The present report provides details and results from Test 1853, which was conducted in UPWT 

Test Section 2 to provide code validation SRP data. This test, conducted in July 2010, 

accomplished 322 runs and 3669 test points, covering 4 model configurations, 3 Mach numbers, 

8 angles of attack, 4 roll angles, multiple tunnel locations, and thrust coefficients up to and 

including 5. The SRP model consisted of a 5 in diameter 70 degree sphere-cone forebody 

followed by a 9.55 in long aftbody. The forebody was designed to allow placement of up to four 

4:1 area ratio nozzles. The primary instrumentation for this test was 174 surface pressure ports, 

125 of which were located on the forebody (including 7 dynamic data sensors), and high-speed 

schlieren video. SRP data was acquired at Mach numbers of 2.4, 3.5, and 4.6. Four model 

configurations were tested, a baseline (all locations plugged), center nozzle (periphery plugged), 

tri-nozzle (center plugged), and quad-nozzle (no plugs). The primary parametrics were a thrust 

coefficient range of 0 to 5 and angles of attack range of –8 to 20 degrees. The intent of this test 

was to generate validation quality data for comparison against CFD modeling techniques. Thus 

the run matrix for this study was carefully crafted to allow for quantification of various sources 

of experimental uncertainty, such as random errors due to run-to-run variations and bias errors 

due to flowfield or model misalignments. To accommodate the uncertainty assessment, many 

repeat runs were conducted with the model at various locations within the tunnel and with the 

model rolled 0, 60, 120, and 180 degrees. All of the schlieren and steady-state pressure data

obtained during Test 1853 are contained within the appendices of this report. Separate papers 

are planned to cover the details of the high frequency data and uncertainty analysis, although 

some results are also contained herein. 

Below is a review of the major findings from Test 1853:

For the baseline configuration,

 the results were as expected, showing a decrease in shock standoff and an increase in 

pressure coefficient as the Mach number is increased;

 the angle of attack effect is to increase windward forebody pressures while decreasing 

leeward;

 the translation and roll data were used as part of the uncertainty assessment.

For the center nozzle configuration,

 the largest forward displacement of the bow shock for a given thrust coefficient was 

provided;

 the thrust coefficients above one were sufficient to establish broad and steady jet plumes 

that mostly shielded the forebody surface from high aerodynamic pressures;

 for angles of attack of 12° and lower, the flowfield remained fairly steady. However, 

higher AOA resulted in highly chaotic plumes and bow shocks;
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

51

 jet plume dimensions were directly related to the jet pressure ratio and independent of 

Mach number and angle of attack.

For the tri nozzle configuration,

 the results, overall, were the least steady of the three blowing configurations;

 the thrust cases included unsteady long penetration mode results at the lower thrust range;

 at thrust coefficients of one and above, short, steady plumes associated with the blunt 

penetration mode largely shielded the forebody from aerodynamic pressure;

 at thrust coefficients above 2, model orientation affected flowfield stability at angles of 

attack greater than 12°;

 unsteady behavior at angle of attack appeared related to a buildup of surface pressure 

between the plumes; inversely, when a single nozzle bisected the windward forebody, 

aerodynamic pressure was diverted and the flow field was steady;

 the results provided for a wider displacement of the bow shock when compared to the 

center nozzle at equivalent jet pressure ratios.

For the quad nozzle configuration,

 the results were slightly less unsteady when compared to the tri nozzle, over the limited 

range of thrust coefficient results tested here;

 an interesting feature was observed just ahead of the jet plumes that were not seen with the 

other blowing configurations;

 the model orientation effects seen at angle of attack were similar to the previous 

observations with the tri nozzle.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

52

 SECTION 6

REFERENCES

1. Braun, R. D., and Manning, R. M., “Mars Exploration Entry, Descent, and Landing 

Challenges,” Journal of Spacecraft and Rockets, Vol. 44, No. 2, 2007, pp. 310–323.

2. Steinfeldt, B. A., Theisinger, J. E., Korzun, A. M., Clark, I. G., Grant, M. J., and Braun, 

R. D., “High Mass Mars Entry, Descent, and Landing Architecture Assessment,” AIAA 

Paper 2009–6684, Sept. 2009.

3. Dwyer Cianciolo, A. M., et al., “Entry, Descent and Landing Systems Analysis Study: 

Phase 1 Report,” NASA TM 2010–216720, July 2010.

4. Edquist, K. T., Dyakonov, A. A., Korzun, A. M., Shidner, J. D., Studak, J. W., Tigges, 

M. A., Kipp, D. M., Prakash, R., Trumble, K. A., Dupzyk, I. C., “Development of 

Supersonic Retro-Propulsion for Future Mars Entry, Descent, and Landing Systems,” 

AIAA Paper 2010–5046, June 2010.

5. Korzun, A. M., and Braun, R. D., “Performance Characterization of Supersonic 

Retropropulsion for High-Mass Mars Entry Systems,” Journal of Spacecraft and Rockets, 

Vol. 47, No. 5, 2010, pp. 836–848.

6. Korzun, A. M., Braun, R. D., and Cruz, J. R., “Survey of Supersonic Retropropulsion 

Technology for Mars Entry, Descent, and Landing,” Journal of Spacecraft and Rockets, 

Vol. 46, No. 5, 2009, pp. 929–937.

7. Jarvinen, P. O., and Adams, R. H., “The Aerodynamic Characteristics of Large Angled 

Cones with Retrorockets,” NASA CR NAS 7–576, Feb. 1970.

8. Trumble, K. A., Schauerhamer, D. G., Kleb, W. L., Carlson, J. R., Buning, P. G., Edquist, 

K. T., and Barnhardt, M. D., “An Initial Assessment of Navier–Stokes Codes Applied to 

Supersonic Retro-Propulsion,” AIAA Paper 2010–5047, June 2010.

9. Trumble, K. A., Schauerhamer, D. G., Kleb, W. L., Carlson, J. R., and Edquist, K. T., 

“Analysis of Navier–Stokes Codes Applied to Supersonic Retro-Propulsion Wind Tunnel 

Test,” IEEE Aerospace Conference Paper No.1471, March 2011.

10. Korzun, A. M., Cordell, Jr., C. E., and Braun, R. D., “Comparison of Inviscid and 

Viscous Aerodynamic Predictions of Supersonic Retropropulsion Flowfields,” AIAA

Paper 2010–5048, June 2010.

11. Cordell, Jr., C. E., Clark, I. G., and Braun, R. D., “CFD Verification of Supersonic 

Retropropulsion for a Central and Peripheral Configuration,” to be published at IEEEAC, 

March 2011.

12. Daso, E. O., Pritchett, V. E., Wang, T. S., Ota, D. K., Blankson, I. M., and Auslender, A. 

H., “Dynamics of Shock Dispersion and Interactions in Supersonic Freestreams with 

Counterflowing Jets,” AIAA Journal, Vol. 47, No. 6, 2009, pp. 1313–1326.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

53

13. Chang, C. L., Venkatachari, B. S., and Cheng, G. C., “Effect of Counterflow Jet on a 

Supersonic Reentry Capsule,” AIAA paper 2006–4776, 2006.

14. Bakhtian, N. M., and Aftosmis, M. J., “Parametric Study of Peripheral Nozzle 

Configurations for Supersonic Retropropulsion,” AIAA Paper 2010–1238, 2010.

15. Nomura, H., Aso, S., and Nishida, M., “Numerical Simulation of Opposing Sonic Jets,” 

Computers and Fluids, Vol. 21, No. 2, 1992, pp. 229–233.

16. Korzun, Ashley M., “Aerodynamic and Performance Characterization of Supersonic 

Retropropulsion for Application to Planetary Entry and Descent.” Ph.D. Thesis, Georgia 

Institute of Technology, May 2012.

17. Aeschliman, D. P. and Oberkampf, W. L., “Experimental Methodology for 

Computational Fluid Dynamics Code Validation,” AIAA Journal, Vol. 36, No. 5, 1998, 

pp. 733–741.

18. Schwartz, R., “ViDI: Virtual Diagnostics Interface, Volume 1 – The Future of Wind 

Tunnel Testing,” NASA/CR–2003–212667, Dec. 2003.

19. Berry, S. A., Laws, C. T., Kleb, W. L., Rhode, M. N., Spells, C., Mccrea, A. C., Trumble, 

K. A., Schauerhamer, D. G., Oberkampf, W. L., “Supersonic Retro-Propulsion 

Experimental Design for Computational Fluid Dynamics Model Validation,” IEEE 

Aerospace Conference Paper No.1499, March 2011.

20. Berry, S. A., Rhode, M. N., Edquist, K. T., and Player, C. J., “Supersonic 

Retropropulsion Experimental Results from the NASA Langley Unitary Plan Wind 

Tunnel,” AIAA Paper 2011–3489, June 2011.

21. Codoni, J. R., and Berry, S. A., “Analysis of Dynamic Data from Supersonic 

Retropropulsion Experiments in NASA Langley’s Unitary Plan Wind Tunnel,” AIAA 

Paper 2012–2706, June 2012.

22. Rhode, M. N. and Oberkampf, W. L., “Estimation of Uncertainty for a Supersonic RetroPropulsion Model Validation Experiment in a Wind Tunnel,” AIAA Paper 2012–2707, 

June 2012.

23. Micol, J.R., “Langley Research Center's Unitary Plan Wind Tunnel: Testing Capabilities 

and Recent Modernization Activities”, AIAA 2001-0456, 2001.

24. Jackson, Jr., C. M., Corlett, W. A., and Monta, W. J., “Description and Calibration of the 

Langley Unitary Plan Wind Tunnel,” NASA TP 1905, Nov. 1981.

25. Wassum, D. L. and Hyman, Jr., C. E. “Procedures and Requirements for Testing in the 

Langley Research Center Unitary Plan Wind Tunnel,” NASA TM 100529, Feb. 1988.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

54

26. Crawford, B. L., “Angle Measurement System (AMS) for Establishing Model Pitch and 

Roll Zero, and Performing Single Axis Angle Comparisons,” AIAA Paper 2007–1162, 

Jan. 2007.

27. Berry, S. A., and Codoni, J. R., “Dynamic Data Analysis of Supersonic Retropropulsion 

Results from NASA Langley’s Unitary Plan Wind Tunnel,” forthcoming NASA report.

28. Kleb, W. L., Carlson, J. R., Buning, P. G., Berry, S. A., Rhode, M. N., Edquist, K. T., 

Schauerhamer, D. G., Trumble, K. A., Sozer, E., “Toward Supersonic Retropropulsion 

CFD Validation,” AIAA Paper 2011–3490, June 2011.

29. Schauerhamer, D.G., Trumble, K.A., Kleb, W.L., Carlson, J.R., Edquist, K.T., 

“Continuing Validation of Computational Fluid Dynamics For Supersonic 

Retropropulsion,” AIAA Paper 2012-0864, Jan 2012.

30. Rhode, M. N. and Oberkampf, W. L., “Estimation of Uncertainty for a Supersonic RetroPropulsion Model Validation Experiment in a Wind Tunnel,” forthcoming NASA report.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

55

APPENDIX A

MODEL DRAWINGS

A1.0 Model Details

This appendix contains details pertaining to the model, including figures and tables of the 

as-built port locations and parameter list definitions, the model drawings, and photos of the parts 

and assemblies taken during the model acceptance check out (6/24/10). The model drawings are 

provided courtesy of Chris Laws, Aeronautics Systems Engineering Branch.

Figure A-1. View from the front of the model.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

56

Figure A-2. View from the port side of the model.

Table A-1. As-built surface pressure port locations.

Port Type

Dimensional Nondimensional

r, in , deg x, in y, in z, in r/R x/L y/L z/L

P001 ESP 0.518 359.912 0.187 0.518 359.912 0.207 0.018 0.207 359.912

P002 ESP 0.665 359.882 0.241 0.665 359.882 0.266 0.023 0.266 359.882

P003 ESP 0.810 359.864 0.294 0.810 359.864 0.324 0.028 0.324 359.864

P004 ESP 1.687 0.053 0.612 1.687 0.053 0.675 0.058 0.675 0.053

P005 ESP 1.831 359.951 0.665 1.831 359.951 0.733 0.063 0.733 359.951

P006 ESP 1.976 359.988 0.718 1.976 359.988 0.790 0.068 0.790 359.988

P007 ESP 2.126 359.995 0.772 2.126 359.995 0.850 0.073 0.850 359.995

P008 ESP 0.665 347.880 0.241 0.665 347.880 0.266 0.023 0.266 347.880

P009 ESP 1.833 348.011 0.666 1.833 348.011 0.733 0.063 0.733 348.011

P010 ESP 1.249 336.009 0.454 1.249 336.009 0.500 0.043 0.500 336.009

P011 ESP 1.833 336.009 0.666 1.833 336.009 0.733 0.063 0.733 336.009

P012 ESP 0.665 329.935 0.241 0.665 329.935 0.266 0.023 0.266 329.935

P013 ESP 0.957 329.965 0.347 0.957 329.965 0.383 0.033 0.383 329.965

P014 ESP 1.249 329.993 0.453 1.249 329.993 0.499 0.043 0.499 329.993

P015 ESP 1.541 329.982 0.560 1.541 329.982 0.616 0.053 0.616 329.982

P016 ESP 1.833 330.001 0.666 1.833 330.001 0.733 0.063 0.733 330.001

P017 ESP 1.245 324.091 0.452 1.245 324.091 0.498 0.043 0.498 324.091
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

57

Port Type

Dimensional Nondimensional

r, in , deg x, in y, in z, in r/R x/L y/L z/L

P018 ESP 1.832 324.105 0.666 1.832 324.105 0.733 0.063 0.733 324.105

P019 ESP 0.664 312.096 0.241 0.664 312.096 0.265 0.023 0.265 312.096

P020 ESP 1.249 312.109 0.451 1.249 312.109 0.500 0.043 0.500 312.109

P021 ESP 1.831 312.080 0.666 1.831 312.080 0.733 0.063 0.733 312.080

P022 ESP 1.248 306.113 0.453 1.248 306.113 0.499 0.043 0.499 306.113

P023 ESP 1.831 306.105 0.665 1.831 306.105 0.732 0.063 0.732 306.105

P024 ESP 0.518 299.970 0.188 0.518 299.970 0.207 0.018 0.207 299.970

P025 ESP 0.664 299.952 0.241 0.664 299.952 0.266 0.023 0.266 299.952

P026 ESP 0.810 299.961 0.294 0.810 299.961 0.324 0.028 0.324 299.961

P027 ESP 0.956 299.983 0.347 0.956 299.983 0.382 0.033 0.382 299.983

P028 ESP 1.102 299.998 0.400 1.102 299.998 0.441 0.038 0.441 299.998

P029 ESP 1.247 300.033 0.453 1.247 300.033 0.499 0.043 0.499 300.033

P030 ESP 1.394 299.984 0.508 1.394 299.984 0.558 0.048 0.558 299.984

P031 ESP 1.543 300.006 0.553 1.543 300.006 0.617 0.052 0.617 300.006

P032 ESP 1.686 300.006 0.613 1.686 300.006 0.675 0.058 0.675 300.006

P033 ESP 1.832 300.010 0.666 1.832 300.010 0.733 0.063 0.733 300.010

P034 ESP 1.978 300.025 0.719 1.978 300.025 0.791 0.068 0.791 300.025

P035 ESP 2.124 300.009 0.772 2.124 300.009 0.850 0.073 0.850 300.009

P036 ESP 1.246 294.106 0.450 1.246 294.106 0.498 0.043 0.498 294.106

P037 ESP 1.831 294.085 0.665 1.831 294.085 0.732 0.063 0.732 294.085

P038 ESP 0.664 288.029 0.241 0.664 288.029 0.265 0.023 0.265 288.029

P039 ESP 1.247 288.087 0.453 1.247 288.087 0.499 0.043 0.499 288.087

P040 ESP 1.831 288.078 0.665 1.831 288.078 0.732 0.063 0.732 288.078

P041 ESP 1.247 276.082 0.453 –1.240 0.132 0.499 0.043 –0.117 0.013

P042 ESP 1.831 276.103 0.666 –1.821 0.195 0.732 0.063 –0.172 0.018

P043 ESP 0.665 269.952 0.241 –0.665 –0.001 0.266 0.023 –0.063 0.000

P044 ESP 0.956 269.997 0.347 –0.956 0.000 0.383 0.033 –0.091 0.000

P045 ESP 1.249 269.970 0.453 –1.249 –0.001 0.499 0.043 –0.118 0.000

P046 ESP 1.540 270.001 0.560 –1.540 0.000 0.616 0.053 –0.146 0.000

P047 ESP 1.832 270.019 0.666 –1.832 0.001 0.733 0.063 –0.174 0.000

P048 ESP 1.247 264.092 0.453 –1.240 –0.128 0.499 0.043 –0.118 –0.012

P049 ESP 1.829 264.118 0.664 –1.819 –0.187 0.731 0.063 –0.172 –0.018

P050 ESP 0.663 252.161 0.241 –0.631 –0.203 0.265 0.023 –0.060 –0.019

P051 ESP 1.830 252.076 0.665 –1.741 –0.563 0.732 0.063 –0.165 –0.053

P052 ESP 1.831 246.110 0.665 –1.674 –0.741 0.732 0.063 –0.159 –0.070

P053 ESP 0.518 239.848 0.188 –0.448 –0.260 0.207 0.018 –0.042 –0.025

P054 ESP 0.661 239.884 0.256 –0.571 –0.331 0.264 0.024 –0.054 –0.031

P055 ESP 0.807 239.948 0.293 –0.699 –0.404 0.323 0.028 –0.066 –0.038

P056 ESP 1.687 240.117 0.613 –1.463 –0.841 0.675 0.058 –0.139 –0.080

P057 ESP 1.831 240.119 0.665 –1.587 –0.912 0.732 0.063 –0.150 –0.086

Table A-1. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

58

Port Type

Dimensional Nondimensional

r, in , deg x, in y, in z, in r/R x/L y/L z/L

P058 ESP 1.979 239.980 0.719 –1.714 –0.990 0.792 0.068 –0.162 –0.094

P059 ESP 2.126 240.055 0.773 –1.842 –1.061 0.850 0.073 –0.175 –0.101

P060 ESP 1.831 234.055 0.665 –1.482 –1.075 0.732 0.063 –0.140 –0.102

P061 ESP 0.663 228.121 0.240 –0.493 –0.442 0.265 0.023 –0.047 –0.042

P062 ESP 1.831 228.098 0.665 –1.362 –1.223 0.732 0.063 –0.129 –0.116

P063 ESP 1.246 216.050 0.452 –0.733 –1.007 0.498 0.043 –0.069 –0.095

P064 ESP 1.830 216.042 0.665 –1.077 –1.480 0.732 0.063 –0.102 –0.140

P065 ESP 0.663 209.938 0.241 –0.331 –0.575 0.265 0.023 –0.031 –0.054

P066 ESP 0.952 210.003 0.346 –0.476 –0.825 0.381 0.033 –0.045 –0.078

P067 ESP 1.246 209.964 0.452 –0.622 –1.080 0.498 0.043 –0.059 –0.102

P068 ESP 1.539 210.030 0.559 –0.770 –1.333 0.616 0.053 –0.073 –0.126

P069 ESP 1.832 210.012 0.665 –0.916 –1.586 0.733 0.063 –0.087 –0.150

P070 ESP 1.247 204.080 0.453 –0.509 –1.139 0.499 0.043 –0.048 –0.108

P071 ESP 1.831 204.086 0.665 –0.747 –1.672 0.732 0.063 –0.071 –0.158

P072 ESP 0.663 192.075 0.240 –0.139 –0.648 0.265 0.023 –0.013 –0.061

P073 ESP 1.247 192.088 0.453 –0.261 –1.219 0.499 0.043 –0.025 –0.116

P074 ESP 1.831 192.048 0.665 –0.382 –1.790 0.732 0.063 –0.036 –0.170

P075 ESP 1.247 186.098 0.453 –0.132 –1.239 0.499 0.043 –0.013 –0.117

P076 ESP 0.518 179.985 0.187 0.000 –0.517 0.207 0.018 0.000 –0.049

P077 ESP 0.663 179.928 0.240 0.001 –0.663 0.265 0.023 0.000 –0.063

P078 ESP 0.810 179.964 0.294 0.001 –0.810 0.324 0.028 0.000 –0.077

P079 ESP 0.955 179.946 0.346 0.001 –0.955 0.382 0.033 0.000 –0.090

P080 ESP 1.101 180.002 0.400 0.000 –1.101 0.440 0.038 0.000 –0.104

P081 ESP 1.247 179.986 0.453 0.000 –1.247 0.499 0.043 0.000 –0.118

P082 ESP 1.393 179.996 0.506 0.000 –1.393 0.557 0.048 0.000 –0.132

P083 ESP 1.539 180.011 0.559 0.000 –1.539 0.616 0.053 0.000 –0.146

P084 ESP 1.685 180.019 0.612 –0.001 –1.685 0.674 0.058 0.000 –0.160

P085 ESP 1.831 180.024 0.665 –0.001 –1.831 0.732 0.063 0.000 –0.173

P086 ESP 1.977 180.002 0.718 0.000 –1.976 0.791 0.068 0.000 –0.187

P087 ESP 2.124 180.062 0.772 –0.002 –2.124 0.850 0.073 0.000 –0.201

P088 ESP 0.663 150.006 0.240 0.332 –0.575 0.265 0.023 0.031 –0.054

P089 ESP 1.247 150.019 0.453 0.623 –1.080 0.499 0.043 0.059 –0.102

P090 ESP 1.831 150.057 0.665 0.914 –1.586 0.732 0.063 0.087 –0.150

P091 ESP 0.663 120.037 0.240 0.574 –0.332 0.265 0.023 0.054 –0.031

P092 ESP 1.831 120.081 0.665 1.584 –0.918 0.732 0.063 0.150 –0.087

P093 ESP 0.665 89.986 0.241 0.665 0.000 0.266 0.023 0.063 0.000

P094 ESP 1.247 90.011 0.453 1.247 0.000 0.499 0.043 0.118 0.000

P095 ESP 1.831 90.032 0.665 1.831 –0.001 0.732 0.063 0.173 0.000

P096 ESP 0.661 59.770 0.239 0.571 0.333 0.264 0.023 0.054 0.032

P097 ESP 0.953 60.019 0.352 0.825 0.476 0.381 0.033 0.078 0.045

Table A-1. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

59

Port Type

Dimensional Nondimensional

r, in , deg x, in y, in z, in r/R x/L y/L z/L

P098 ESP 1.244 59.968 0.451 1.077 0.622 0.498 0.043 0.102 0.059

P099 ESP 1.541 59.927 0.560 1.333 0.772 0.616 0.053 0.126 0.073

P100 ESP 1.829 60.083 0.664 1.585 0.912 0.732 0.063 0.150 0.086

P101 ESP 2.125 59.963 0.772 1.840 1.064 0.850 0.073 0.174 0.101

P102 ESP 0.661 29.615 0.240 0.327 0.575 0.265 0.023 0.031 0.054

P103 ESP 1.245 29.845 0.452 0.619 1.080 0.498 0.043 0.059 0.102

P104 ESP 1.831 29.897 0.665 0.913 1.587 0.732 0.063 0.086 0.150

P105 Kulite 2.124 282.015 0.772 –2.078 0.442 0.850 0.073 –0.197 0.042

P106 Kulite 2.125 186.074 0.772 –0.225 –2.113 0.850 0.073 –0.021 –0.200

P107 Kulite 1.832 156.086 0.666 0.743 –1.675 0.733 0.063 0.070 –0.159

P108 Kulite 2.122 132.064 0.771 1.576 –1.422 0.849 0.073 0.149 –0.135

P109 Kulite 1.247 84.071 0.454 1.241 0.129 0.499 0.043 0.118 0.012

P110 Kulite 1.832 48.055 0.665 1.362 1.224 0.733 0.063 0.129 0.116

P111 Kulite 1.832 23.988 0.666 0.745 1.674 0.733 0.063 0.071 0.159

P112 ESP 0.003 193.032 0.064 –0.001 –0.003 0.001 0.006 0.000 0.000

P113 ESP 0.185 0.858 0.081 0.003 0.184 0.074 0.008 0.000 0.017

P114 ESP 0.184 299.589 0.081 –0.160 0.091 0.074 0.008 –0.015 0.009

P115 ESP 0.186 240.067 0.081 –0.161 –0.093 0.075 0.008 –0.015 –0.009

P116 ESP 0.189 180.584 0.082 –0.002 –0.189 0.075 0.008 0.000 –0.018

P117 ESP 1.102 0.008 0.400 0.000 1.102 0.441 0.038 0.000 0.104

P118 ESP 1.247 0.095 0.453 0.002 1.247 0.499 0.043 0.000 0.118

P119 ESP 1.393 0.077 0.506 0.002 1.393 0.557 0.048 0.000 0.132

P120 ESP 1.249 354.175 0.453 –0.127 1.242 0.499 0.043 –0.012 0.118

P121 ESP 1.252 5.978 0.456 0.130 1.245 0.501 0.043 0.012 0.118

P122 ESP 1.103 240.074 0.399 –0.956 –0.550 0.441 0.038 –0.091 –0.052

P123 ESP 1.248 240.024 0.452 –1.081 –0.624 0.499 0.043 –0.102 –0.059

P124 ESP 1.393 240.068 0.505 –1.207 –0.695 0.557 0.048 –0.114 –0.066

P125 ESP 1.250 234.004 0.453 –1.011 –0.735 0.500 0.043 –0.096 –0.070

P126 Kulite 2.500 307.062 1.162 –1.995 1.507 1.000 0.110 –0.189 0.143

P127 Kulite 2.500 220.768 1.119 –1.632 –1.893 1.000 0.106 –0.155 –0.179

P128 ESP 2.500 360.579 2.480 0.025 2.500 1.000 0.235 0.002 0.237

P129 ESP 2.500 348.440 2.478 –0.501 2.449 1.000 0.235 –0.047 0.232

P130 ESP 2.500 336.302 2.476 –1.005 2.289 1.000 0.235 –0.095 0.217

P131 ESP 2.500 324.184 2.477 –1.463 2.027 1.000 0.235 –0.139 0.192

P132 ESP 2.500 312.333 2.474 –1.848 1.684 1.000 0.234 –0.175 0.159

P133 ESP 2.500 300.226 2.479 –2.160 1.259 1.000 0.235 –0.205 0.119

P134 ESP 2.500 288.203 2.479 –2.375 0.781 1.000 0.235 –0.225 0.074

P135 ESP 2.500 276.125 2.478 –2.486 0.267 1.000 0.235 –0.235 0.025

P136 ESP 2.500 264.090 2.477 –2.487 –0.257 1.000 0.235 –0.236 –0.024

P137 ESP 2.500 252.130 2.474 –2.379 –0.767 1.000 0.234 –0.225 –0.073

Table A-1. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

60

Port Type

Dimensional Nondimensional

r, in , deg x, in y, in z, in r/R x/L y/L z/L

P138 ESP 2.500 239.942 2.477 –2.164 –1.252 1.000 0.235 –0.205 –0.119

P139 ESP 2.500 227.932 2.473 –1.856 –1.675 1.000 0.234 –0.176 –0.159

P140 ESP 2.500 216.069 2.479 –1.472 –2.021 1.000 0.235 –0.139 –0.191

P141 ESP 2.500 203.793 2.476 –1.009 –2.288 1.000 0.235 –0.096 –0.217

P142 ESP 2.500 191.795 2.480 –0.511 –2.447 1.000 0.235 –0.048 –0.232

P143 ESP 2.500 180.256 2.491 –0.011 –2.500 1.000 0.236 –0.001 –0.237

P144 ESP 2.500 300.113 2.977 –2.163 1.254 1.000 0.282 –0.205 0.119

P145 ESP 2.500 239.924 2.978 –2.163 –1.253 1.000 0.282 –0.205 –0.119

P146 ESP 2.500 180.294 2.977 –0.013 –2.500 1.000 0.282 –0.001 –0.237

P147 ESP 2.500 360.421 3.477 0.018 2.500 1.000 0.329 0.002 0.237

P148 ESP 2.500 330.250 3.477 –1.241 2.170 1.000 0.329 –0.118 0.206

P149 ESP 2.500 300.048 3.477 –2.164 1.252 1.000 0.329 –0.205 0.119

P150 ESP 2.500 269.957 3.477 –2.500 –0.002 1.000 0.329 –0.237 0.000

P151 ESP 2.500 240.105 3.477 –2.167 –1.246 1.000 0.329 –0.205 –0.118

P152 ESP 2.500 209.816 3.473 –1.243 –2.169 1.000 0.329 –0.118 –0.205

P153 ESP 2.500 180.200 3.479 –0.009 –2.500 1.000 0.330 –0.001 –0.237

P154 ESP 2.500 300.222 4.726 –2.160 1.258 1.000 0.448 –0.205 0.119

P155 ESP 2.500 239.994 4.729 –2.165 –1.250 1.000 0.448 –0.205 –0.118

P156 ESP 2.500 180.347 4.725 –0.015 –2.500 1.000 0.448 –0.001 –0.237

P157 ESP 2.500 360.411 5.977 0.018 2.500 1.000 0.566 0.002 0.237

P158 ESP 2.500 330.307 5.977 –1.238 2.172 1.000 0.566 –0.117 0.206

P159 ESP 2.500 300.190 5.982 –2.161 1.257 1.000 0.567 –0.205 0.119

P160 ESP 2.500 270.062 5.979 –2.500 0.003 1.000 0.566 –0.237 0.000

P161 ESP 2.500 240.009 5.977 –2.165 –1.250 1.000 0.566 –0.205 –0.118

P162 ESP 2.500 209.944 5.977 –1.248 –2.166 1.000 0.566 –0.118 –0.205

P163 ESP 2.500 180.240 5.979 –0.010 –2.500 1.000 0.566 –0.001 –0.237

P164 ESP 2.500 300.185 7.224 –2.161 1.257 1.000 0.684 –0.205 0.119

P165 ESP 2.500 239.951 7.224 –2.164 –1.252 1.000 0.684 –0.205 –0.119

P166 ESP 2.500 180.274 7.229 –0.012 –2.500 1.000 0.685 –0.001 –0.237

P167 ESP 2.500 360.478 8.481 0.021 2.500 1.000 0.803 0.002 0.237

P168 ESP 2.500 330.308 8.480 –1.238 2.172 1.000 0.803 –0.117 0.206

P169 ESP 2.500 300.032 8.478 –2.164 1.251 1.000 0.803 –0.205 0.119

P170 ESP 2.500 270.200 8.480 –2.500 0.009 1.000 0.803 –0.237 0.001

P171 ESP 2.500 239.946 8.478 –2.164 –1.252 1.000 0.803 –0.205 –0.119

P172 ESP 2.500 209.803 8.478 –1.243 –2.169 1.000 0.803 –0.118 –0.206

P173 ESP 2.500 180.183 8.470 –0.008 –2.500 1.000 0.802 –0.001 –0.237

P174 ESP 2.500 300.084 9.733 –2.163 1.253 1.000 0.922 –0.205 0.119

P175 ESP 2.500 240.005 9.732 –2.165 –1.250 1.000 0.922 –0.205 –0.118

P176 ESP 2.500 180.326 9.731 –0.014 –2.500 1.000 0.922 –0.001 –0.237

Table A-1. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

61

Table A-2. Parameter list and definitions.

(a) Logistical and reference.

# NAME VALUE UNITS DESCRIPTION EQUATION

1 TEST 1853 – Test number constant

2 RUN – Run number set value

3 POINT – Point number set value

4 ACQDATE –

Data acquisition date 

(yyyymmdd)

e.g., May 18, 

2009 = 20090518

5 ACQTIME –

Data acquisition time, 

CDT (hhmmss) e.g. 2:54:32 PM = 145432

6 DATAREV –

Data reduction revision 

number (beginning at 0) set value

7 CONFIGCO – Model configuration ID

set value: 0 = no nozzles; 

1 = Nozzle 1; 2 = Nozzles 

2,3,4; 3 = Nozzles 1,2,3,4

8 FAC 8 – Facility identifier number constant

9 SREF 0.13635 ft^2 Aerodynamic reference 

area (Aref)

constant

10 LREF 0.41667 ft Aerodynamic reference 

length constant

11 THAFA deg Pitch plane flow angle 

w.r.t gravity axis system facility method

12 PSIFA deg Yaw plane flow angle 

w.r.t gravity axis system facility method
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

62

Table A-2. Continued.

(b) Model attitude and location.

# NAME VALUE UNITS DESCRIPTION EQUATION

13 THASS deg Support system pitch angle 

w.r.t. gravity axis system facility measurement

14 PSISS deg Support system yaw angle 

w.r.t. gravity axis system facility measurement

15 PHISS deg Support system roll angle 

w.r.t. gravity axis system facility measurement

16 QFLEX deg Measured model Q-Flex 

pitch angle facility measurement

17 ALPHA deg Model angle of attack facility method

18 BETA deg Model angle of sideslip facility method

19 PHI deg Model angle of roll PHI = 

atan(tan(BETA)/sin(ALPHA))

20 ALPHAT deg Total angle of attack ALPHAT = 

acos(cos(ALPHA)*cos(BETA))

21 XSS in

Test section x axis position 

of model nose at zero AOA, 

including axial movement of 

model support system

facility method

22 YSS in

Test section y axis position 

of model nose at zero AOA, 

including lateral movement 

of model support system

facility method

23 ZSS in Test section z axis position 

of model nose at zero AOA facility method

24 DXSS in

Change in test section x

axis position of model nose 

with pitch angle, relative to 

model support system

DXSS = XMODEL – XSS

25 DYSS in

Change in test section y

axis position of model nose 

with yaw angle, relative to 

model support system

DYSS = YMODEL – YSS

26 DZSS in

Change in test section z

axis position of model nose 

with pitch angle, relative to 

model support system

DZSS = ZMODEL – ZSS

27 XMODEL in Test section x axis position 

of model nose facility method; Euler rotations

28 YMODEL in Test section y axis position 

of model nose facility method; Euler rotations

29 ZMODEL in Test section z axis position 

of model nose facility method; Euler rotations
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

63

Table A-2. Continued.

(c) Facility flow conditions and tunnel wall pressures.

# NAME VALUE UNITS DESCRIPTION EQUATION

30 MACH – Free-stream Mach number facility method

31 PTINF psfa Facility stilling chamber total 

pressure

facility measurement

32 TTINF Rankine Facility stilling chamber total 

temperature facility measurement

33 DEWPOINT Rankine

Dewpoint temperature 

measured in facility stilling 

chamber

facility measurement

34 SPHUMID

lbm 

H20/lbm 

air

Free-stream specific 

humidity facility method

35 PINF psfa Free-stream static pressure facility method

36 TINF Rankine Free-stream static 

temperature facility method

37 RHOINF slug/ft^3 Free-stream density facility method

38 QINF psfa Free-stream dynamic 

pressure

facility method

39 VINF ft/sec Free-stream velocity facility method

40 REINF 1/ft Free-stream unit Reynolds 

number facility method

41 RED –

Free-stream Reynolds 

number, based on reference 

length

RED = REINF*LREF

42 GAMMA 1.400 – Ratio of specific heats constant

43 RGAS 1716.59

ftlbf/(slugR)

Gas constant, air constant

44 SPRINF –

Free-stream normal shock 

static pressure ratio

SPRINF = 1 + 

2*GAMMA/(GAMMA + 

1)*(MACH^2 – 1)

45 SDRINF –

Free-stream normal shock 

density ratio

SDRINF = (GAMMA + 

1)*MACH^2/((GAMMA – 1)

*MACH^2 + 2)

46 PT2 psfa Free-stream post-normalshock stagnation pressure

PT2 = PTINF*SPRINF^(–1/

(GAMMA – 1))

*SDRINF^(GAMMA/ 

(GAMMA – 1))

47 TT2 Rankine

Free-stream post-normalshock stagnation 

temperature

TT2 = TTINF
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

64

# NAME VALUE UNITS DESCRIPTION EQUATION

48 MACH2 –

Free-stream post-normalshock Mach number

MACH2 = sqrt((1 + 0.5

*(GAMMA – 1)*MACH^2)/

(GAMMA*MACH^2 –

0.5*(GAMMA – 1))

49 P2 psfa Free-stream post-normalshock static pressure P2 = PINF*SPRINF

50 T2 Rankine Free-stream post-normalshock static temperature T2 = TINF*SPRINF/SDRINF

51 RHO2 slug/ft^3 Free-stream post-normalshock density RHO2 = RHOINF*SDRINF

52 V2 ft/sec Free-stream post-normalshock velocity V2 = VINF/SDRINF

53 Q2 psfa Free-stream post-normalshock dynamic pressure Q2 = 0.5*RHO2*V2^2

54 PWALL01 psia

Test section wall static 

pressure #76, X = 32.6875, 

Y = 3.0

facility measurement

55 PWALL02 psia

Test section wall static 

pressure #75, X = 39.6875, 

Y = 3.0

facility measurement

56 PWALL03 psia

Test section wall static 

pressure #74, X = 46.6875, 

Y = 3.0

facility measurement

57 PWALL04 psia

Test section wall static 

pressure #73, X = 53.6875, 

Y = 3.0

facility measurement

58 PWALL05 psia

Test section wall static 

pressure #72, X = 60.6875, 

Y = 3.0

facility measurement

59 PWALL06 psia

Test section wall static 

pressure #71, X = 67.1875, 

Y = 3.0

facility measurement

60 PWALL07 psia

Test section wall static 

pressure #70, X = 73.1875, 

Y = 3.0

facility measurement

61 PWALL08 psia

Test section wall static 

pressure #69, X = 92.7500, 

Y = 3.0

facility measurement

62 PWALL09 psia

Test section wall static 

pressure #68, X = 97.7500, 

Y = 3.0

facility measurement

63 PWALL10 psia

Test section wall static 

pressure #67, X = 

109.8125, Y = 3.0

facility measurement

Table A-2. Continued.

(c) Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

65

Table A-2. Continued.

(d) Model thermocouple temperatures.

# NAME VALUE UNITS DESCRIPTION EQUATION

64 TMODEL1 deg F Model temperature #1, Type K 

thermocouple, TOP facility measurement

65 TMODEL2 deg F Model temperature #2, Type K 

thermocouple, STARBOARD facility measurement

66 TMODEL3 deg F Model temperature #3, Type K 

thermocouple, BOTTOM facility measurement

67 TMODEL4 deg F Model temperature #4, Type K 

thermocouple, PORT facility measurement

68 TQFLEX deg F Temperature beneath Q-Flex, 

Type K thermocouple facility measurement

(e) Model plenum conditions.

# NAME VALUE UNITS DESCRIPTION EQUATION

69 PPLENA psia

Measured plenum static 

pressure A, plenum 

upstream (relative to HPA 

flow) Kulite XT–190–

2000A, 7700–7–152

facility measurement

70 PPLENB psia

Measured plenum static 

pressure B, plenum 

downstream (relative to 

HPA flow) Kulite XT–190–

2000A, 7700–7–151

facility measurement

71 PPLEN1 psia

Measured plenum static 

pressure in Nozzle #1 

(center nozzle)

facility measurement; 

PPLEN1 = IJ1*(transducer 

calibration function)

72 PPLEN2 psia

Measured plenum static 

pressure in Nozzle #2 

(half radius nozzle, 0 deg 

orientation)

facility measurement; 

PPLEN2 = IJ2*(transducer 

calibration function)

73 TTJA Rankine

Measured plenum total 

temperature A, RTD probe, 

plenum upstream (relative 

to HPA flow)

facility measurement

74 TTJ1 Rankine

Measured plenum total 

temperature in Nozzle #1, 

Type K thermocouple

facility measurement; TTJ1 = 

IJ1*(thermocouple calibration 

function)
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

66

# NAME VALUE UNITS DESCRIPTION EQUATION

75 TTJ2 Rankine

Measured plenum total 

temperature in Nozzle #2, 

Type K thermocouple

facility measurement; TTJ2 = 

IJ2*(thermocouple calibration 

function)

76 GAMMAP –

Ratio of specific heats 

evaluated at plenum static 

conditions

GASPROPS – user input 

method 3 (PTJ, TTJ); 

GASPROPS output variable 

= GAMMA1

77 APLENA 0.78540 in^2 Cross-sectional area of 

model plenum at station A constant

78 APLENB 0.89185 in^2 Cross-sectional area of 

model plenum at station B constant

79 APLEN1 0.19635 in^2 Cross-sectional area of 

model plenum in Nozzle #1 constant

80 APLEN2 0.19635 in^2 Cross-sectional area of 

model plenum in Nozzle #2 constant

81 MPLENA –

Model plenum Mach 

number at station A

MPLENA = WVEN/GC *sqrt

(TTJA*RGASJ/GAMMAP)

/(PPLENA*APLENA)

82 MPLENB –

Model plenum Mach 

number at station B

MPLENB = WVEN /GC*

sqrt(TTJA*RGASJ/GAMMAP)

/(PPLENB*APLENB)

83 MPLEN1 –

Model plenum Mach 

number in Nozzle #1

MPLEN1 = IJ1*WVEN/GC*

ATHROTJ1/ATHROTJT*sqrt

(TTJ1*RGASJ/GAMMAP)

/(PPLEN1*APLEN1)

84 MPLEN2 –

Model plenum Mach 

number in Nozzle #2

MPLEN2 = IJ2*WVEN

/GC*ATHROTJ2/ATHROTJT*

sqrt(TTJ2*RGASJ/GAMMAP)

/(PPLEN2 *APLEN2)

85 PTJA psia Plenum total pressure at 

station A

PTJA = PPLENA*(1 + 0.5

*(GAMMAP – 1)

*MPLENA^2)^(GAMMAP

/(GAMMAP – 1))

86 PTJB psia Plenum total pressure at 

station B

PTJB = PPLENB*(1 + 0.5

*(GAMMAP – 1)

*MPLENB^2)^(GAMMAP

/(GAMMAP – 1))

87 PTJ1 psia Plenum total pressure in 

Nozzle #1

PTJ1 = IJ1*PPLEN1*(1 + 0.5

*(GAMMAP – 1)

*MPLEN1^2)^(GAMMAP

/(GAMMAP – 1))

88 PTJ2 psia Plenum total pressure in 

Nozzle #2

PTJ2 = IJ2*PPLEN2*(1 + 0.5

*(GAMMAP – 1)

*MPLEN2^2)^(GAMMAP

/(GAMMAP – 1))

Table A-2. Continued.

(e) Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

67

Table A-2. Continued.

(f) Facility venturi measurements.

# NAME VALUE UNITS DESCRIPTION EQUATION

89 GC 32.17405 lbm/slug Mass units 

conversion factor constant

90 DVEN1 1.50300 in Venturi upstream 

diameter constant

91 DVEN2 0.69500 in Venturi throat 

diameter constant

92 AVEN1 1.77422 in^2 Venturi upstream 

area

constant

93 AVEN2 0.37937 in^2 Venturi throat area constant

94 BETAVEN 0.46241 –

Venturi diameter 

ratio (BETAVEN = 

DVEN2/DVEN1)

constant

95 PVEN1 psia Venturi upstream 

static pressure facility measurement

96 TVEN1 Rankine Venturi upstream 

static temperature facility measurement

97 ZVEN1 –

Venturi upstream 

compressibility 

factor, evaluated

at PVEN1 & 

TVEN3 conditions

GASPROPS–user input method 

3 (PVEN1, TVEN1); GASPROPS 

output variable = Z1

98 RHOVEN1 slug/ft^3 Venturi upstream 

static density

GASPROPS–user input method 

3 (PVEN1, TVEN1); GASPROPS 

output variable = RH1

99 MUVEN1 lbfsec/ft^2

Venturi 

downstream 

viscosity

GASPROPS–user input method 

3 (PVEN1, TVEN1); GASPROPS 

output variable = MU1

100 GAMMAVEN –

Venturi ratio of 

specific heats 

evaluated at 

upstream 

conditions

GASPROPS–user input method 

3 (PVEN1, TVEN1); GASPROPS 

output variable = GAMMA1

101 PVEN2 psia Venturi throat 

static pressure PVEN2 = PVEN1 - PDIFFVEN

102 PDIFFVEN psia

Venturi upstreamto-throat static 

pressure 

differential 

(PVEN1–PVEN2)

facility measurement
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

68

# NAME VALUE UNITS DESCRIPTION EQUATION

103 PRATVEN –

Venturi throat-toupstream static 

pressure ratio

PRATVEN = PVEN2/PVEN1

104 WVENHYD lbm/sec

Venturi 

incompressible 

mass flow rate 

(Hydraulic 

Equation)

WVENHYD = 

GC*AVEN2/144*sqrt(2*RHOVEN

1*144*PDIFFVEN

/(1–BETAVEN^4))

105 YVEN –

Venturi expansion 

factor

YVEN = sqrt(GAMMAVEN

/(GAMMAVEN–1)*PRATVEN

^(2/GAMMAVEN)*(1–PRATVEN

^((GAMMAVEN–1)

/GAMMAVEN))*(1–BETAVEN^4)

/((1-PRATVEN)*(1–BETAVEN^4

*PRATVEN^(2/GAMMAVEN))))

106 WVENIDEL lbm/sec Venturi ideal mass 

flow rate WVENIDEL = YVEN*WVENHYD

107 REVEN2 –

Venturi throat 

Reynolds number

REVEN2 = 

4/GC*WVEN/(PI*DVEN2/12*MU

VEN1)

108 CDVEN –

Venturi discharge 

coefficient

CDVEN = b0 + b1*REVEN2 + b2/

sqrt(REVEN2); where 'b' 

coefficients are given in 'Venturi 

Cd Table' page

109 WVEN lbm/sec Venturi mass flow 

rate WVEN = CDVEN*WVENIDEL

110 WDCV lbm/sec

Digital control 

valve mass flow 

rate

facility method (from digital 

control valve)

(g) Model nozzle calculations.

# NAME VALUE UNITS DESCRIPTION EQUATION

111 REALGAS –

Flag to denote 

method used for 

calculation of nozzle 

exit conditions 

(IDEAL GAS = 0, 

REAL GAS = 1)

set value

112 IJ1 –

Flag to denote 

presence of nozzle #1 

in model 

(OFF = 0, ON = 1)

set value

Table A-2. Continued.

(f) Facility venturi measurements.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

69

# NAME VALUE UNITS DESCRIPTION EQUATION

113 IJ2 –

Flag to denote 

presence of nozzle #2 

in model 

(OFF = 0, ON = 1)

set value

114 IJ3 –

Flag to denote 

presence of nozzle #3 

in model 

(OFF = 0, ON = 1)

set value

115 IJ4 –

Flag to denote 

presence of nozzle #4 

in model 

(OFF = 0, ON = 1)

set value

116 DTHROTJ

1

0.2491 in Nozzle throat 

diameter, nozzle #1 constant

117 DTHROTJ

2

0.2498 in Nozzle throat 

diameter, nozzle #2 constant

118 DTHROTJ

3

0.2535 in Nozzle throat 

diameter, nozzle #3 constant

119 DTHROTJ

4

0.2503 in Nozzle throat 

diameter, nozzle #4 constant

120 DEXITJ1 0.5014 in Nozzle virtual exit 

diameter, nozzle #1 constant

121 DEXITJ2 0.4965 in Nozzle virtual exit 

diameter, nozzle #2 constant

122 DEXITJ3 0.4989 in Nozzle virtual exit 

diameter, nozzle #3 constant

123 DEXITJ4 0.4996 in Nozzle virtual exit 

diameter, nozzle #4 constant

124 ATHROTJ1 0.048735 in^2 Nozzle throat area, 

nozzle #1 constant

125 ATHROTJ2 0.049009 in^2 Nozzle throat area, 

nozzle #2 constant

126 ATHROTJ3 0.050471 in^2 Nozzle throat area, 

nozzle #3 constant

127 ATHROTJ4 0.049205 in^2 Nozzle throat area, 

nozzle #4 constant

128 AEXITJ1 0.197451 in^2 Nozzle virtual exit 

area, nozzle #1 constant

129 AEXITJ2 0.193610 in^2 Nozzle virtual exit 

area, nozzle #2 constant

130 AEXITJ3 0.195487 in^2 Nozzle virtual exit 

area, nozzle #3 constant

131 AEXITJ4 0.196036 in^2 Nozzle virtual exit 

area, nozzle #4 constant

132 ARATIOJ1 4.051550 –

Nozzle exit-to-throat 

area ratio, nozzle #1 constant

Table A-2. Continued.

(g) Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

70

# NAME VALUE UNITS DESCRIPTION EQUATION

133 ARATIOJ2 3.950514 –

Nozzle exit-to-throat 

area ratio, nozzle #2 constant

134 ARATIOJ3 3.873210 –

Nozzle exit-to-throat 

area ratio, nozzle #3 constant

135 ARATIOJ4 3.984035 –

Nozzle exit-to-throat 

area ratio, nozzle #4 constant

136 THETAWJ

1

14.981 deg Nozzle exit wall 

angle, nozzle #1 constant

137 THETAWJ

2

14.977 deg Nozzle exit wall 

angle, nozzle #2 constant

138 THETAWJ

3

14.994 deg Nozzle exit wall 

angle, nozzle #3 constant

139 THETAWJ

4

14.985 deg Nozzle exit wall 

angle, nozzle #4 constant

140 LAMBDAJ1 0.98301 –

Streamline spreading 

momentum correction 

factor, nozzle #1

constant

141 LAMBDAJ2 0.98302 –

Streamline spreading 

momentum correction 

factor, nozzle #2

constant

142 LAMBDAJ3 0.98298 –

Streamline spreading 

momentum correction 

factor, nozzle #3

constant

143 LAMBDAJ4 0.98300 –

Streamline spreading 

momentum correction 

factor, nozzle #4

constant

144 ATHROTJ

T

in^2

Total nozzle throat 

area of nozzles 

present in model

ATHROTJT = 

dotproduct(ATHROTJ(i),IJ(i))

145 RGASJ 1716.59 ft-lbf/

(slug-R) Gas constant, air constant

146 PTJ psia Average measured 

plenum total pressure PTJ = average(PTJA:PTJB)

147 TTJ Rankine

Average measured 

plenum total 

temperature

TTJ = TTJA

148 GAMMAT –

Nozzle throat specific 

heat ratio (assumes 

choked flow at nozzle 

throat)

GASPROPS – user input 

method 1 (PTJ, TTJ, 

MACH = 1); GASPROPS 

output variable = GAMMA1

149 NPRJ – Nozzle pressure ratio NPRJ = PTJ/PINF*144

150 NTRJ –

Nozzle temperature 

ratio NTRJ = TTJ/TINF

151 WTAPJ –

Nozzle mass flow 

function (assumes 

choked flow at nozzle 

throat)

WTAPJ = sqrt

(GAMMAT/RGASJ*(2/(GAMM

AT + 1))^((GAMMAT + 1)

/(GAMMAT – 1)))

Table A-2. Continued.

(g) Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

71

# NAME VALUE UNITS DESCRIPTION EQUATION

152 WIDEALJ lbm/sec

Nozzle net ideal mass 

flow (assumes 

choked flow at nozzle 

throat)

WIDEALJ = 

GC*WTAPJ*PTJ*ATHROTJT/

sqrt(TTJ)

153 CDISJ –

Nozzle net discharge 

coefficient CDISJ = WVEN/WIDEALJ

154 NPRJ_PT1 –

Nozzle pressure ratio, 

referenced to facility 

total pressure

NPRJ_PT1 = PTJ/PTINF*144

155 NRPJ_PT2 –

Nozzle pressure ratio, 

referenced to postnormal-shock 

stagnation pressure

NRPJ_PT2 = PTJ/PT2*144

156 NPRJ_P2 –

Nozzle pressure ratio, 

referenced to postnormal-shock static 

pressure

NPRJ_P2 = PTJ/P2*144

157 M0J1 2.9571 –

Ideal gas nozzle exit 

Mach number, 

nozzle #1

constant

158 M0J2 2.9305 –

Ideal gas nozzle exit 

Mach number, 

nozzle #2

constant

159 M0J3 2.9097 –

Ideal gas nozzle exit 

Mach number, 

nozzle #3

constant

160 M0J4 2.9394 –

Ideal gas nozzle exit 

Mach number, 

nozzle #4

constant

161 MEXITJ1 –

Nozzle exit Mach 

number, nozzle #1

MEXITJ1 = IJ1*M0J1*(A0 + 

A1*PTJ + A2*PTJ^2); “A” 

constants found in Nozzle 

Mexit Variation, cells K74:M77

162 MEXITJ2 –

Nozzle exit Mach 

number, nozzle #2

MEXITJ2 = IJ2*M0J2*(A0 + 

A1*PTJ + A2*PTJ^2); “A” 

constants found in Nozzle 

Mexit Variation, cells K74:M77

163 MEXITJ3 –

Nozzle exit Mach 

number, nozzle #3

MEXITJ3 = IJ3*M0J3*(A0 + 

A1*PTJ + A2*PTJ^2); “A” 

constants found in Nozzle 

Mexit Variation, cells K74:M77

164 MEXITJ4 –

Nozzle exit Mach 

number, nozzle #4

MEXITJ4 = IJ4*M0J4*(A0 + 

A1*PTJ + A2*PTJ^2); “A” 

constants found in Nozzle 

Mexit Variation, cells K74:M77

Table A-2. Continued.

(g) Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

72

# NAME VALUE UNITS DESCRIPTION EQUATION

165 GAMMAJ1 –

Nozzle exit specific 

heat ratio, nozzle #1

GASPROPS – user input 

method 1 (PTJ, TTJ, 

MEXITJ1); GASPROPS output 

variable = GAMMA1; 

GAMMAJ1 = IJ1*

(GASPROPS output)

166 GAMMAJ2 –

Nozzle exit specific 

heat ratio, nozzle #2

GASPROPS – user input 

method 1 (PTJ, TTJ, 

MEXITJ2); GASPROPS output 

variable = GAMMA1; 

GAMMAJ2 = IJ2*

(GASPROPS output)

167 GAMMAJ3 –

Nozzle exit specific 

heat ratio, nozzle #3

GASPROPS – user input 

method 1 (PTJ, TTJ, 

MEXITJ3); GASPROPS output 

variable = GAMMA1; 

GAMMAJ3 = IJ3*

(GASPROPS output)

168 GAMMAJ4 –

Nozzle exit specific 

heat ratio, nozzle #4

GASPROPS – user input 

method 1 (PTJ, TTJ, 

MEXITJ4); GASPROPS output 

variable = GAMMA1; 

GAMMAJ4 = IJ4*

(GASPROPS output)

169 PJ1 psia Nozzle exit static 

pressure, nozzle #1

GASPROPS – user input 

method 1 (PTJ, TTJ, 

MEXITJ1); GASPROPS output 

variable = P1; PJ1 = IJ1*

(GASPROPS output)

170 PJ2 psia Nozzle exit static 

pressure, nozzle #2

GASPROPS – user input 

method 1 (PTJ, TTJ, 

MEXITJ2); GASPROPS output 

variable = P1; PJ2 = IJ2*

(GASPROPS output)

171 PJ3 psia Nozzle exit static 

pressure, nozzle #3

GASPROPS – user input 

method 1 (PTJ, TTJ, 

MEXITJ3); GASPROPS output 

variable = P1; PJ3 = IJ3*

(GASPROPS output)

172 PJ4 psia Nozzle exit static 

pressure, nozzle #4

GASPROPS – user input 

method 1 (PTJ, TTJ, 

MEXITJ4); GASPROPS output 

variable = P1; PJ4 = IJ4*

(GASPROPS output)

Table A-2. Continued.

(g) Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

73

# NAME VALUE UNITS DESCRIPTION EQUATION

173 TJ1 Rankine

Nozzle exit static 

temperature, nozzle 

#1

GASPROPS – user input 

method 1 (PTJ, TTJ, 

MEXITJ1); GASPROPS output 

variable = T1; TJ1 = IJ1*

(GASPROPS output)

174 TJ2 Rankine

Nozzle exit static 

temperature, nozzle 

#2

GASPROPS – user input 

method 1 (PTJ, TTJ, 

MEXITJ2); GASPROPS output 

variable = T1; TJ2 = IJ2*

(GASPROPS output)

175 TJ3 Rankine

Nozzle exit static 

temperature, nozzle 

#3

GASPROPS – user input 

method 1 (PTJ, TTJ, 

MEXITJ3); GASPROPS output 

variable = T1; TJ3 = IJ3*

(GASPROPS output)

176 TJ4 Rankine

Nozzle exit static 

temperature, nozzle 

#4

GASPROPS – user input 

method 1 (PTJ, TTJ, 

MEXITJ4); GASPROPS output 

variable = T1; TJ4 = IJ4*

(GASPROPS output)

177 VJ1 ft/sec Nozzle exit velocity, 

nozzle #1

GASPROPS – user input 

method 1 (PTJ, TTJ, 

MEXITJ1); GASPROPS output 

variable = U1; VJ1 = IJ1*

(GASPROPS output)

178 VJ2 ft/sec Nozzle exit velocity, 

nozzle #2

GASPROPS – user input 

method 1 (PTJ, TTJ, 

MEXITJ2); GASPROPS output 

variable = U1; VJ2 = IJ2*

(GASPROPS output)

179 VJ3 ft/sec Nozzle exit velocity, 

nozzle #3

GASPROPS – user input 

method 1 (PTJ, TTJ, 

MEXITJ3); GASPROPS output 

variable = U1; VJ3 = IJ3

*(GASPROPS output)

180 VJ4 ft/sec Nozzle exit velocity, 

nozzle #4

GASPROPS–user input 

method 1 (PTJ, TTJ, 

MEXITJ4); GASPROPS output 

variable = U1; VJ4 = IJ4*

(GASPROPS output)

181 WJ1 lbm/sec Nozzle mass flow 

rate, nozzle #1

WJ1 = IJ1*WVEN

*ATHROTJ1/ATHROTJT

182 WJ2 lbm/sec Nozzle mass flow 

rate, nozzle #2

WJ2 = IJ2*WVEN

*ATHROTJ2/ATHROTJT

183 WJ3 lbm/sec Nozzle mass flow 

rate, nozzle #3

WJ3 = IJ3*WVEN

*ATHROTJ3/ATHROTJT

184 WJ4 lbm/sec Nozzle mass flow 

rate, nozzle #4

WJ4 = IJ4*WVEN

*ATHROTJ4/ATHROTJT

Table A-2. Continued.

(g) Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

74

# NAME VALUE UNITS DESCRIPTION EQUATION

185 WVJ1 lbf Nozzle momentum 

flux, nozzle #1 WVJ1 = WJ1/GC*VJ1

186 WVJ2 lbf Nozzle momentum 

flux, nozzle #2 WVJ2 = WJ2/GC*VJ2

187 WVJ3 lbf Nozzle momentum 

flux, nozzle #3 WVJ3 = WJ3/GC*VJ3

188 WVJ4 lbf Nozzle momentum 

flux, nozzle #4 WVJ4 = WJ4/GC*VJ4

189 FVACJ1 lbf Nozzle thrust, 

nozzle #1

FVACJ1 = LAMBDAJ1*WVJ1 + 

PJ1*AEXITJ1

190 FVACJ2 lbf Nozzle thrust, 

nozzle #2

FVACJ2 = LAMBDAJ2*WVJ2 + 

PJ2*AEXITJ2

191 FVACJ3 lbf Nozzle thrust, 

nozzle #3

FVACJ3 = LAMBDAJ3*WVJ3 + 

PJ3*AEXITJ3

192 FVACJ4 lbf Nozzle thrust, 

nozzle #4

FVACJ4 = LAMBDAJ4*WVJ4 + 

PJ4*AEXITJ4

193 CTJ1 –

Nozzle thrust 

coefficient, nozzle #1 CTJ1 = FVACJ1/(QINF*SREF)

194 CTJ2 –

Nozzle thrust 

coefficient, nozzle #2 CTJ2 = FVACJ2/(QINF*SREF)

195 CTJ3 –

Nozzle thrust 

coefficient, nozzle #3 CTJ3 = FVACJ3/(QINF*SREF)

196 CTJ4 –

Nozzle thrust 

coefficient, nozzle #4 CTJ4 = FVACJ4/(QINF*SREF)

197 PRATJ1 –

Nozzle exit-to-freestream static 

pressure ratio, nozzle 

#1

PRATJ1 = PJ1/PINF*144

198 PRATJ2 –

Nozzle exit-to-freestream static 

pressure ratio, nozzle 

#2

PRATJ2 = PJ2/PINF*144

199 PRATJ3 –

Nozzle exit-to-freestream static 

pressure ratio, nozzle 

#3

PRATJ3 = PJ3/PINF*144

200 PRATJ4 –

Nozzle exit-to-freestream static 

pressure ratio, nozzle 

#4

PRATJ4 = PJ4/PINF*144

201 FVACJTOT lbf Total nozzle thrust FVACJTOT = 

sum(FVACJ1:FVACJ4)

202 CTJTOT lbf Total nozzle thrust 

coefficient CTJTOT = sum(CTJ1:CTJ4)

Table A-2. Continued.

(g) Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

75

Table A-2. Continued.

(h) ESP auxiliary measurements.

# NAME VALUE UNITS DESCRIPTION EQUATION

203 ESPREF psia

Reference pressure 

supplied to ESP module in 

LAT

facility measurement

204 ESPTEMP2 deg F Measured temperature 

from ESP module #1 facility measurement

205 ESPTEMP3 deg F Measured temperature 

from ESP module #2 facility measurement

206 ESPTEMP4 deg F Measured temperature 

from ESP module #3 facility measurement

207 PMON1 psia

Monitor pressure #1 from 

facility-supplied pressure 

standard

facility measurement

208 PMON2 psia

Monitor pressure #2 from 

facility-supplied pressure 

standard

facility measurement

209 PMON3 psia

Monitor pressure #3 from 

facility-supplied pressure 

standard

facility measurement

210 ESPMON21 psia Measurement of PMON1 

by ESP module #2 facility measurement

211 ESPMON22 psia Measurement of PMON2 

by ESP module #2 facility measurement

212 ESPMON23 psia Measurement of PMON3 

by ESP module #2 facility measurement

213 ESPMON31 psia Measurement of PMON1 

by ESP module #3 facility measurement

214 ESPMON32 psia Measurement of PMON2 

by ESP module #3 facility measurement

215 ESPMON33 psia Measurement of PMON3 

by ESP module #3 facility measurement

216 ESPMON41 psia Measurement of PMON1 

by ESP module #4 facility measurement

217 ESPMON42 psia Measurement of PMON2 

by ESP module #4 facility measurement

218 ESPMON43 psia Measurement of PMON3 

by ESP module #4 facility measurement

219 DESPM21 psia

Difference between 

measured ESP pressure in 

module #2 and supplied 

monitor pressure 1

DESPM21 =

ESPMON21 – PMON1
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

76

# NAME VALUE UNITS DESCRIPTION EQUATION

220 DESPM22 psia

Difference between 

measured ESP pressure in 

module #2 and supplied 

monitor pressure 2

DESPM22 =

ESPMON22 – PMON2

221 DESPM23 psia

Difference between 

measured ESP pressure in 

module #2 and supplied 

monitor pressure 3

DESPM23 =

ESPMON23 – PMON3

222 DESPM31 psia

Difference between 

measured ESP pressure in 

module #3 and supplied 

monitor pressure 1

DESPM31 =

ESPMON31 –PMON1

223 DESPM32 psia

Difference between 

measured ESP pressure in 

module #3 and supplied 

monitor pressure 2

DESPM32 =

ESPMON32 – PMON2

224 DESPM33 psia

Difference between 

measured ESP pressure in 

module #3 and supplied 

monitor pressure 3

DESPM33 =

ESPMON33 – PMON3

225 DESPM41 psia

Difference between 

measured ESP pressure in 

module #4 and supplied 

monitor pressure 1

DESPM41 =

ESPMON41 –PMON1

226 DESPM42 psia

Difference between 

measured ESP pressure in 

module #4 and supplied 

monitor pressure 2

DESPM42 =

ESPMON42 – PMON2

227 DESPM43 psia

Difference between 

measured ESP pressure in 

module #4 and supplied 

monitor pressure 3

DESPM43 =

ESPMON43 – PMON3

(i) Model surface static pressures.

# NAME VALUE UNITS DESCRIPTION EQUATION

228 P001 psia Model surface pressure – ESP facility measurement

229 P002 psia Model surface pressure – ESP facility measurement

230 P003 psia Model surface pressure – ESP facility measurement

231 P004 psia Model surface pressure – ESP facility measurement

232 P005 psia Model surface pressure – ESP facility measurement

233 P006 psia Model surface pressure – ESP facility measurement

Table A-2. Continued.

(h) Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

77

# NAME VALUE UNITS DESCRIPTION EQUATION

234 P007 psia Model surface pressure – ESP facility measurement

235 P008 psia Model surface pressure – ESP facility measurement

236 P009 psia Model surface pressure – ESP facility measurement

237 P010 psia Model surface pressure – ESP facility measurement

238 P011 psia Model surface pressure – ESP facility measurement

239 P012 psia Model surface pressure – ESP facility measurement

240 P013 psia Model surface pressure – ESP facility measurement

241 P014 psia Model surface pressure – ESP facility measurement

242 P015 psia Model surface pressure – ESP facility measurement

243 P016 psia Model surface pressure – ESP facility measurement

244 P017 psia Model surface pressure – ESP facility measurement

245 P018 psia Model surface pressure – ESP facility measurement

246 P019 psia Model surface pressure – ESP facility measurement

247 P020 psia Model surface pressure – ESP facility measurement

248 P021 psia Model surface pressure – ESP facility measurement

249 P022 psia Model surface pressure – ESP facility measurement

250 P023 psia Model surface pressure – ESP facility measurement

251 P024 psia Model surface pressure – ESP facility measurement

252 P025 psia Model surface pressure – ESP facility measurement

253 P026 psia Model surface pressure – ESP facility measurement

254 P027 psia Model surface pressure – ESP facility measurement

255 P028 psia Model surface pressure – ESP facility measurement

256 P029 psia Model surface pressure – ESP facility measurement

257 P030 psia Model surface pressure – ESP facility measurement

258 P031 psia Model surface pressure – ESP facility measurement

259 P032 psia Model surface pressure – ESP facility measurement

260 P033 psia Model surface pressure – ESP facility measurement

261 P034 psia Model surface pressure – ESP facility measurement

262 P035 psia Model surface pressure – ESP facility measurement

263 P036 psia Model surface pressure – ESP facility measurement

264 P037 psia Model surface pressure – ESP facility measurement

265 P038 psia Model surface pressure – ESP facility measurement

266 P039 psia Model surface pressure – ESP facility measurement

267 P040 psia Model surface pressure – ESP facility measurement

268 P041 psia Model surface pressure – ESP facility measurement

269 P042 psia Model surface pressure – ESP facility measurement

270 P043 psia Model surface pressure – ESP facility measurement

271 P044 psia Model surface pressure – ESP facility measurement

Table A-2. Continued.

(i) Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

78

# NAME VALUE UNITS DESCRIPTION EQUATION

272 P045 psia Model surface pressure – ESP facility measurement

273 P046 psia Model surface pressure – ESP facility measurement

274 P047 psia Model surface pressure – ESP facility measurement

275 P048 psia Model surface pressure – ESP facility measurement

276 P049 psia Model surface pressure – ESP facility measurement

277 P050 psia Model surface pressure – ESP facility measurement

278 P051 psia Model surface pressure – ESP facility measurement

279 P052 psia Model surface pressure – ESP facility measurement

280 P053 psia Model surface pressure – ESP facility measurement

281 P054 psia Model surface pressure – ESP facility measurement

282 P055 psia Model surface pressure – ESP facility measurement

283 P056 psia Model surface pressure – ESP facility measurement

284 P057 psia Model surface pressure – ESP facility measurement

285 P058 psia Model surface pressure – ESP facility measurement

286 P059 psia Model surface pressure – ESP facility measurement

287 P060 psia Model surface pressure – ESP facility measurement

288 P061 psia Model surface pressure – ESP facility measurement

289 P062 psia Model surface pressure – ESP facility measurement

290 P063 psia Model surface pressure – ESP facility measurement

291 P064 psia Model surface pressure – ESP facility measurement

292 P065 psia Model surface pressure – ESP facility measurement

293 P066 psia Model surface pressure – ESP facility measurement

294 P067 psia Model surface pressure – ESP facility measurement

295 P068 psia Model surface pressure – ESP facility measurement

296 P069 psia Model surface pressure – ESP facility measurement

297 P070 psia Model surface pressure – ESP facility measurement

298 P071 psia Model surface pressure – ESP facility measurement

299 P072 psia Model surface pressure – ESP facility measurement

300 P073 psia Model surface pressure – ESP facility measurement

301 P074 psia Model surface pressure – ESP facility measurement

302 P075 psia Model surface pressure – ESP facility measurement

303 P076 psia Model surface pressure – ESP facility measurement

304 P077 psia Model surface pressure – ESP facility measurement

305 P078 psia Model surface pressure – ESP facility measurement

306 P079 psia Model surface pressure – ESP facility measurement

307 P080 psia Model surface pressure – ESP facility measurement

308 P081 psia Model surface pressure – ESP facility measurement

309 P082 psia Model surface pressure – ESP facility measurement

Table A-2. Continued.

(i) Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

79

# NAME VALUE UNITS DESCRIPTION EQUATION

310 P083 psia Model surface pressure – ESP facility measurement

311 P084 psia Model surface pressure – ESP facility measurement

312 P085 psia Model surface pressure – ESP facility measurement

313 P086 psia Model surface pressure – ESP facility measurement

314 P087 psia Model surface pressure – ESP facility measurement

315 P088 psia Model surface pressure – ESP facility measurement

316 P089 psia Model surface pressure – ESP facility measurement

317 P090 psia Model surface pressure – ESP facility measurement

318 P091 psia Model surface pressure – ESP facility measurement

319 P092 psia Model surface pressure – ESP facility measurement

320 P093 psia Model surface pressure – ESP facility measurement

321 P094 psia Model surface pressure – ESP facility measurement

322 P095 psia Model surface pressure – ESP facility measurement

323 P096 psia Model surface pressure – ESP facility measurement

324 P097 psia Model surface pressure – ESP facility measurement

325 P098 psia Model surface pressure – ESP facility measurement

326 P099 psia Model surface pressure – ESP facility measurement

327 P100 psia Model surface pressure – ESP facility measurement

328 P101 psia Model surface pressure – ESP facility measurement

329 P102 psia Model surface pressure – ESP facility measurement

330 P103 psia Model surface pressure – ESP facility measurement

331 P104 psia Model surface pressure – ESP facility measurement

332 P105 psia Model surface pressure – Kulite 

XCS–062–5A, 7822–7–336 facility measurement

333 P106 psia Model surface pressure – Kulite 

XCS–062–5A, 7822–7–325 facility measurement

334 P107 psia Model surface pressure – Kulite 

XCS–062–5A, 7822–7–329 facility measurement

335 P108 psia Model surface pressure – Kulite 

XCS–062–5A, 7822–7–327 facility measurement

336 P109 psia Model surface pressure – Kulite 

XCS–062–5A, 7822–7–324 facility measurement

337 P110 psia Model surface pressure – Kulite 

XCS–062–5A, 7822–7–323 facility measurement

338 P111 psia Model surface pressure – Kulite 

XCS–062–5A, 7822–7–322 facility measurement

339 P112 psia Model surface pressure – ESP facility measurement

340 P113 psia Model surface pressure – ESP facility measurement

341 P114 psia Model surface pressure – ESP facility measurement

Table A-2. Continued.

(i) Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

80

# NAME VALUE UNITS DESCRIPTION EQUATION

342 P115 psia Model surface pressure – ESP facility measurement

343 P116 psia Model surface pressure – ESP facility measurement

344 P117 psia Model surface pressure – ESP facility measurement

345 P118 psia Model surface pressure – ESP facility measurement

346 P119 psia Model surface pressure – ESP facility measurement

347 P120 psia Model surface pressure – ESP facility measurement

348 P121 psia Model surface pressure – ESP facility measurement

349 P122 psia Model surface pressure – ESP facility measurement

350 P123 psia Model surface pressure – ESP facility measurement

351 P124 psia Model surface pressure – ESP facility measurement

352 P125 psia Model surface pressure – ESP facility measurement

353 P126 999 psia Model surface pressure – Kulite 

XCS–062–5A, 7822–7–331

constant (since no longer 

operable as destroyed 

7/2/10 during installation)

354 P127 999 psia Model surface pressure – Kulite 

XCS–062–5A, 7822–7–328

constant (since no longer 

operable as destroyed 

7/2/10 during installation)

355 P128 psia Model surface pressure – ESP facility measurement

356 P129 psia Model surface pressure – ESP facility measurement

357 P130 psia Model surface pressure – ESP facility measurement

358 P131 psia Model surface pressure – ESP facility measurement

359 P132 psia Model surface pressure – ESP facility measurement

360 P133 psia Model surface pressure – ESP facility measurement

361 P134 psia Model surface pressure – ESP facility measurement

362 P135 psia Model surface pressure – ESP facility measurement

363 P136 psia Model surface pressure – ESP facility measurement

364 P137 psia Model surface pressure – ESP facility measurement

365 P138 psia Model surface pressure – ESP facility measurement

366 P139 psia Model surface pressure – ESP facility measurement

367 P140 psia Model surface pressure – ESP facility measurement

368 P141 psia Model surface pressure – ESP facility measurement

369 P142 psia Model surface pressure – ESP facility measurement

370 P143 psia Model surface pressure – ESP facility measurement

371 P144 psia Model surface pressure – ESP facility measurement

372 P145 psia Model surface pressure – ESP facility measurement

373 P146 psia Model surface pressure – ESP facility measurement

374 P147 psia Model surface pressure – ESP facility measurement

375 P148 psia Model surface pressure – ESP facility measurement

Table A-2. Continued.

(i) Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

81

# NAME VALUE UNITS DESCRIPTION EQUATION

376 P149 psia Model surface pressure – ESP facility measurement

377 P150 psia Model surface pressure – ESP facility measurement

378 P151 psia Model surface pressure – ESP facility measurement

379 P152 psia Model surface pressure – ESP facility measurement

380 P153 psia Model surface pressure – ESP facility measurement

381 P154 psia Model surface pressure – ESP facility measurement

382 P155 psia Model surface pressure – ESP facility measurement

383 P156 psia Model surface pressure – ESP facility measurement

384 P157 psia Model surface pressure – ESP facility measurement

385 P158 psia Model surface pressure – ESP facility measurement

386 P159 psia Model surface pressure – ESP facility measurement

387 P160 psia Model surface pressure – ESP facility measurement

388 P161 psia Model surface pressure – ESP facility measurement

389 P162 psia Model surface pressure – ESP facility measurement

390 P163 psia Model surface pressure – ESP facility measurement

391 P164 psia Model surface pressure – ESP facility measurement

392 P165 psia Model surface pressure – ESP facility measurement

393 P166 psia Model surface pressure – ESP facility measurement

394 P167 psia Model surface pressure – ESP facility measurement

395 P168 psia Model surface pressure – ESP facility measurement

396 P169 psia Model surface pressure – ESP facility measurement

397 P170 psia Model surface pressure – ESP facility measurement

398 P171 psia Model surface pressure – ESP facility measurement

399 P172 psia Model surface pressure – ESP facility measurement

400 P173 psia Model surface pressure – ESP facility measurement

401 P174 psia Model surface pressure – ESP facility measurement

402 P175 psia Model surface pressure – ESP facility measurement

403 P176 psia Model surface pressure – ESP facility measurement

(j) Model surface static pressure coefficients.

# NAME VALUE UNITS DESCRIPTION EQUATION

404 CP001 –

Model surface pressure 

coefficient – ESP

CP001 = (P001*144 –

PINF)/QINF

405 CP002 –

Model surface pressure 

coefficient – ESP

CP002 = (P002*144 –

PINF)/QINF

406 CP003 –

Model surface pressure 

coefficient – ESP

CP003 = (P003*144 –

PINF)/QINF

Table A-2. Continued.

(i) Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

82

# NAME VALUE UNITS DESCRIPTION EQUATION

407 CP004 –

Model surface pressure 

coefficient – ESP

CP004 = (P004*144 –

PINF)/QINF

408 CP005 –

Model surface pressure 

coefficient – ESP

CP005 = (P005*144 –

PINF)/QINF

409 CP006 –

Model surface pressure 

coefficient – ESP

CP006 = (P006*144 –

PINF)/QINF

410 CP007 –

Model surface pressure 

coefficient – ESP

CP007 = (P007*144 –

PINF)/QINF

411 CP008 –

Model surface pressure 

coefficient – ESP

CP008 = (P008*144 –

PINF)/QINF

412 CP009 –

Model surface pressure 

coefficient – ESP

CP009 = (P009*144 –

PINF)/QINF

413 CP010 –

Model surface pressure 

coefficient – ESP

CP010 = (P010*144 –

PINF)/QINF

414 CP011 –

Model surface pressure 

coefficient – ESP

CP011 = (P011*144 –

PINF)/QINF

415 CP012 –

Model surface pressure 

coefficient – ESP

CP012 = (P012*144 –

PINF)/QINF

416 CP013 –

Model surface pressure 

coefficient – ESP

CP013 = (P013*144 –

PINF)/QINF

417 CP014 –

Model surface pressure 

coefficient – ESP

CP014 = (P014*144 –

PINF)/QINF

418 CP015 –

Model surface pressure 

coefficient – ESP

CP015 = (P015*144 –

PINF)/QINF

419 CP016 –

Model surface pressure 

coefficient – ESP

CP016 = (P016*144 –

PINF)/QINF

420 CP017 –

Model surface pressure 

coefficient – ESP

CP017 = (P017*144 –

PINF)/QINF

421 CP018 –

Model surface pressure 

coefficient – ESP

CP018 = (P018*144 –

PINF)/QINF

422 CP019 –

Model surface pressure 

coefficient – ESP

CP019 = (P019*144 –

PINF)/QINF

423 CP020 –

Model surface pressure 

coefficient – ESP

CP020 = (P020*144 –

PINF)/QINF

424 CP021 –

Model surface pressure 

coefficient – ESP

CP021 = (P021*144 –

PINF)/QINF

425 CP022 –

Model surface pressure 

coefficient – ESP

CP022 = (P022*144 –

PINF)/QINF

426 CP023 –

Model surface pressure 

coefficient – ESP

CP023 = (P023*144 –

PINF)/QINF

427 CP024 –

Model surface pressure 

coefficient – ESP

CP024 = (P024*144 –

PINF)/QINF

Table A-2. Continued.

(j) Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

83

# NAME VALUE UNITS DESCRIPTION EQUATION

428 CP025 –

Model surface pressure 

coefficient – ESP

CP025 = (P025*144 –

PINF)/QINF

429 CP026 –

Model surface pressure 

coefficient – ESP

CP026 = (P026*144 –

PINF)/QINF

430 CP027 –

Model surface pressure 

coefficient – ESP

CP027 = (P027*144 –

PINF)/QINF

431 CP028 –

Model surface pressure 

coefficient – ESP

CP028 = (P028*144 –

PINF)/QINF

432 CP029 –

Model surface pressure 

coefficient – ESP

CP029 = (P029*144 –

PINF)/QINF

433 CP030 –

Model surface pressure 

coefficient – ESP

CP030 = (P030*144 –

PINF)/QINF

434 CP031 –

Model surface pressure 

coefficient – ESP

CP031 = (P031*144 –

PINF)/QINF

435 CP032 –

Model surface pressure 

coefficient – ESP

CP032 = (P032*144 –

PINF)/QINF

436 CP033 –

Model surface pressure 

coefficient – ESP

CP033 = (P033*144 –

PINF)/QINF

437 CP034 –

Model surface pressure 

coefficient – ESP

CP034 = (P034*144 –

PINF)/QINF

438 CP035 –

Model surface pressure 

coefficient – ESP

CP035 = (P035*144 –

PINF)/QINF

439 CP036 –

Model surface pressure 

coefficient – ESP

CP036 = (P036*144 –

PINF)/QINF

440 CP037 –

Model surface pressure 

coefficient – ESP

CP037 = (P037*144 –

PINF)/QINF

441 CP038 –

Model surface pressure 

coefficient – ESP

CP038 = (P038*144 –

PINF)/QINF

442 CP039 –

Model surface pressure 

coefficient – ESP

CP039 = (P039*144 –

PINF)/QINF

443 CP040 –

Model surface pressure 

coefficient – ESP

CP040 = (P040*144 –

PINF)/QINF

444 CP041 –

Model surface pressure 

coefficient – ESP

CP041 = (P041*144 –

PINF)/QINF

445 CP042 –

Model surface pressure 

coefficient – ESP

CP042 = (P042*144 –

PINF)/QINF

446 CP043 –

Model surface pressure 

coefficient – ESP

CP043 = (P043*144 –

PINF)/QINF

447 CP044 –

Model surface pressure 

coefficient – ESP

CP044 = (P044*144 –

PINF)/QINF

448 CP045 –

Model surface pressure 

coefficient – ESP

CP045 = (P045*144 –

PINF)/QINF

Table A-2. Continued.

(j) Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

84

# NAME VALUE UNITS DESCRIPTION EQUATION

449 CP046 –

Model surface pressure 

coefficient – ESP

CP046 = (P046*144 –

PINF)/QINF

450 CP047 –

Model surface pressure 

coefficient – ESP

CP047 = (P047*144 –

PINF)/QINF

451 CP048 –

Model surface pressure 

coefficient – ESP

CP048 = (P048*144 –

PINF)/QINF

452 CP049 –

Model surface pressure 

coefficient – ESP

CP049 = (P049*144 –

PINF)/QINF

453 CP050 –

Model surface pressure 

coefficient – ESP

CP050 = (P050*144 –

PINF)/QINF

454 CP051 –

Model surface pressure 

coefficient – ESP

CP051 = (P051*144 –

PINF)/QINF

455 CP052 –

Model surface pressure 

coefficient – ESP

CP052 = (P052*144 –

PINF)/QINF

456 CP053 –

Model surface pressure 

coefficient – ESP

CP053 = (P053*144 –

PINF)/QINF

457 CP054 –

Model surface pressure 

coefficient – ESP

CP054 = (P054*144 –

PINF)/QINF

458 CP055 –

Model surface pressure 

coefficient – ESP

CP055 = (P055*144 –

PINF)/QINF

459 CP056 –

Model surface pressure 

coefficient – ESP

CP056 = (P056*144 –

PINF)/QINF

460 CP057 –

Model surface pressure 

coefficient – ESP

CP057 = (P057*144 –

PINF)/QINF

461 CP058 –

Model surface pressure 

coefficient – ESP

CP058 = (P058*144 –

PINF)/QINF

462 CP059 –

Model surface pressure 

coefficient – ESP

CP059 = (P059*144 –

PINF)/QINF

463 CP060 –

Model surface pressure 

coefficient – ESP

CP060 = (P060*144 –

PINF)/QINF

464 CP061 –

Model surface pressure 

coefficient – ESP

CP061 = (P061*144 –

PINF)/QINF

465 CP062 –

Model surface pressure 

coefficient – ESP

CP062 = (P062*144 –

PINF)/QINF

466 CP063 –

Model surface pressure 

coefficient – ESP

CP063 = (P063*144 –

PINF)/QINF

467 CP064 –

Model surface pressure 

coefficient – ESP

CP064 = (P064*144 –

PINF)/QINF

468 CP065 –

Model surface pressure 

coefficient – ESP

CP065 = (P065*144 –

PINF)/QINF

469 CP066 –

Model surface pressure 

coefficient – ESP

CP066 = (P066*144 –

PINF)/QINF

Table A-2. Continued.

(j) Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

85

# NAME VALUE UNITS DESCRIPTION EQUATION

470 CP067 –

Model surface pressure 

coefficient – ESP

CP067 = (P067*144 –

PINF)/QINF

471 CP068 –

Model surface pressure 

coefficient – ESP

CP068 = (P068*144 –

PINF)/QINF

472 CP069 –

Model surface pressure 

coefficient – ESP

CP069 = (P069*144 –

PINF)/QINF

473 CP070 –

Model surface pressure 

coefficient – ESP

CP070 = (P070*144 –

PINF)/QINF

474 CP071 –

Model surface pressure 

coefficient – ESP

CP071 = (P071*144 –

PINF)/QINF

475 CP072 –

Model surface pressure 

coefficient – ESP

CP072 = (P072*144 –

PINF)/QINF

476 CP073 –

Model surface pressure 

coefficient – ESP

CP073 = (P073*144 –

PINF)/QINF

477 CP074 Model surface pressure 

coefficient – ESP

CP074 = (P074*144 –

PINF)/QINF

478 CP075 Model surface pressure 

coefficient – ESP

CP075 = (P075*144 –

PINF)/QINF

479 CP076 Model surface pressure 

coefficient – ESP

CP076 = (P076*144 –

PINF)/QINF

480 CP077 Model surface pressure 

coefficient – ESP

CP077 = (P077*144 –

PINF)/QINF

481 CP078 Model surface pressure 

coefficient – ESP

CP078 = (P078*144 –

PINF)/QINF

482 CP079 Model surface pressure 

coefficient – ESP

CP079 = (P079*144 –

PINF)/QINF

483 CP080 Model surface pressure 

coefficient – ESP

CP080 = (P080*144 –

PINF)/QINF

484 CP081 Model surface pressure 

coefficient – ESP

CP081 = (P081*144 –

PINF)/QINF

485 CP082 Model surface pressure 

coefficient – ESP

CP082 = (P082*144 –

PINF)/QINF

486 CP083 Model surface pressure 

coefficient – ESP

CP083 = (P083*144 –

PINF)/QINF

487 CP084 Model surface pressure 

coefficient – ESP

CP084 = (P084*144 –

PINF)/QINF

488 CP085 Model surface pressure 

coefficient – ESP

CP085 = (P085*144 –

PINF)/QINF

489 CP086 Model surface pressure 

coefficient – ESP

CP086 = (P086*144 –

PINF)/QINF

490 CP087 Model surface pressure 

coefficient – ESP

CP087 = (P087*144 –

PINF)/QINF

Table A-2. Continued.

(j) Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

86

# NAME VALUE UNITS DESCRIPTION EQUATION

491 CP088 Model surface pressure 

coefficient – ESP

CP088 = (P088*144 –

PINF)/QINF

492 CP089 Model surface pressure 

coefficient – ESP

CP089 = (P089*144 –

PINF)/QINF

493 CP090 Model surface pressure 

coefficient – ESP

CP090 = (P090*144 –

PINF)/QINF

494 CP091 Model surface pressure 

coefficient – ESP

CP091 = (P091*144 –

PINF)/QINF

495 CP092 Model surface pressure 

coefficient – ESP

CP092 = (P092*144 –

PINF)/QINF

496 CP093 Model surface pressure 

coefficient – ESP

CP093 = (P093*144 –

PINF)/QINF

497 CP094 Model surface pressure 

coefficient – ESP

CP094 = (P094*144 –

PINF)/QINF

498 CP095 Model surface pressure 

coefficient – ESP

CP095 = (P095*144 –

PINF)/QINF

499 CP096 Model surface pressure 

coefficient – ESP

CP096 = (P096*144 –

PINF)/QINF

500 CP097 Model surface pressure 

coefficient – ESP

CP097 = (P097*144 –

PINF)/QINF

501 CP098 Model surface pressure 

coefficient – ESP

CP098 = (P098*144 –

PINF)/QINF

502 CP099 Model surface pressure 

coefficient – ESP

CP099 = (P099*144 –

PINF)/QINF

503 CP100 Model surface pressure 

coefficient – ESP

CP100 = (P100*144 –

PINF)/QINF

504 CP101 Model surface pressure 

coefficient – ESP

CP101 = (P101*144 –

PINF)/QINF

505 CP102 Model surface pressure 

coefficient – ESP

CP102 = (P102*144 –

PINF)/QINF

506 CP103 Model surface pressure 

coefficient – ESP

CP103 = (P103*144 –

PINF)/QINF

507 CP104 Model surface pressure 

coefficient – ESP

CP104 = (P104*144 –

PINF)/QINF

508 CP105 Model surface pressure 

coefficient – Kulite

CP105 = (P105*144 –

PINF)/QINF

509 CP106 Model surface pressure 

coefficient – Kulite

CP106 = (P106*144 –

PINF)/QINF

510 CP107 Model surface pressure 

coefficient – Kulite

CP107 = (P107*144 –

PINF)/QINF

511 CP108 Model surface pressure 

coefficient – Kulite

CP108 = (P108*144 –

PINF)/QINF

Table A-2. Continued.

(j) Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

87

# NAME VALUE UNITS DESCRIPTION EQUATION

512 CP109 Model surface pressure 

coefficient – Kulite

CP109 = (P109*144 –

PINF)/QINF

513 CP110 Model surface pressure 

coefficient – Kulite

CP110 = (P110*144 –

PINF)/QINF

514 CP111 Model surface pressure 

coefficient – Kulite

CP111 = (P111*144 –

PINF)/QINF

515 CP112 Model surface pressure 

coefficient – ESP

CP112 = (P112*144 –

PINF)/QINF

516 CP113 Model surface pressure 

coefficient – ESP

CP113 = (P113*144 –

PINF)/QINF

517 CP114 Model surface pressure 

coefficient – ESP

CP114 = (P114*144 –

PINF)/QINF

518 CP115 Model surface pressure 

coefficient – ESP

CP115 = (P115*144 –

PINF)/QINF

519 CP116 Model surface pressure 

coefficient – ESP

CP116 = (P116*144 –

PINF)/QINF

520 CP117 Model surface pressure 

coefficient – ESP

CP117 = (P117*144 –

PINF)/QINF

521 CP118 Model surface pressure 

coefficient – ESP

CP118 = (P118*144 –

PINF)/QINF

522 CP119 Model surface pressure 

coefficient – ESP

CP119 = (P119*144 –

PINF)/QINF

523 CP120 Model surface pressure 

coefficient – ESP

CP120 = (P120*144 –

PINF)/QINF

524 CP121 Model surface pressure 

coefficient – ESP

CP121 = (P121*144 –

PINF)/QINF

525 CP122 Model surface pressure 

coefficient – ESP

CP122 = (P122*144 –

PINF)/QINF

526 CP123 Model surface pressure 

coefficient – ESP

CP123 = (P123*144 –

PINF)/QINF

527 CP124 Model surface pressure 

coefficient – ESP

CP124 = (P124*144 –

PINF)/QINF

528 CP125 Model surface pressure 

coefficient – ESP

CP125 = (P125*144 –

PINF)/QINF

529 CP126 999 Model surface pressure 

coefficient – Kulite

constant (since no longer 

operable)

530 CP127 999 Model surface pressure 

coefficient – Kulite

constant (since no longer 

operable)

531 CP128 Model surface pressure 

coefficient – ESP

CP128 = (P128*144 –

PINF)/QINF

532 CP129 Model surface pressure 

coefficient – ESP

CP129 = (P129*144 –

PINF)/QINF

Table A-2. Continued.

(j) Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

88

# NAME VALUE UNITS DESCRIPTION EQUATION

533 CP130 Model surface pressure 

coefficient – ESP

CP130 = (P130*144 –

PINF)/QINF

534 CP131 Model surface pressure 

coefficient – ESP

CP131 = (P131*144 –

PINF)/QINF

535 CP132 Model surface pressure 

coefficient – ESP

CP132 = (P132*144 –

PINF)/QINF

536 CP133 Model surface pressure 

coefficient – ESP

CP133 = (P133*144 –

PINF)/QINF

537 CP134 Model surface pressure 

coefficient – ESP

CP134 = (P134*144 –

PINF)/QINF

538 CP135 Model surface pressure 

coefficient – ESP

CP135 = (P135*144 –

PINF)/QINF

539 CP136 Model surface pressure 

coefficient – ESP

CP136 = (P136*144 –

PINF)/QINF

540 CP137 Model surface pressure 

coefficient – ESP

CP137 = (P137*144 –

PINF)/QINF

541 CP138 Model surface pressure 

coefficient – ESP

CP138 = (P138*144 –

PINF)/QINF

542 CP139 Model surface pressure 

coefficient – ESP

CP139 = (P139*144 –

PINF)/QINF

543 CP140 Model surface pressure 

coefficient – ESP

CP140 = (P140*144 –

PINF)/QINF

544 CP141 Model surface pressure 

coefficient – ESP

CP141 = (P141*144 –

PINF)/QINF

545 CP142 Model surface pressure 

coefficient – ESP

CP142 = (P142*144 –

PINF)/QINF

546 CP143 Model surface pressure 

coefficient – ESP

CP143 = (P143*144 –

PINF)/QINF

547 CP144 Model surface pressure 

coefficient – ESP

CP144 = (P144*144 –

PINF)/QINF

548 CP145 Model surface pressure 

coefficient – ESP

CP145 = (P145*144 –

PINF)/QINF

549 CP146 Model surface pressure 

coefficient – ESP

CP146 = (P146*144 –

PINF)/QINF

550 CP147 Model surface pressure 

coefficient – ESP

CP147 = (P147*144 –

PINF)/QINF

551 CP148 Model surface pressure 

coefficient – ESP

CP148 = (P148*144 –

PINF)/QINF

552 CP149 Model surface pressure 

coefficient – ESP

CP149 = (P149*144 –

PINF)/QINF

553 CP150 Model surface pressure 

coefficient – ESP

CP150 = (P150*144 –

PINF)/QINF

Table A-2. Continued.

(j) Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

89

# NAME VALUE UNITS DESCRIPTION EQUATION

554 CP151 Model surface pressure 

coefficient – ESP

CP151 = (P151*144 –

PINF)/QINF

555 CP152 Model surface pressure 

coefficient – ESP

CP152 = (P152*144 –

PINF)/QINF

556 CP153 Model surface pressure 

coefficient – ESP

CP153 = (P153*144 –

PINF)/QINF

557 CP154 Model surface pressure 

coefficient – ESP

CP154 = (P154*144 –

PINF)/QINF

558 CP155 Model surface pressure 

coefficient – ESP

CP155 = (P155*144 –

PINF)/QINF

559 CP156 Model surface pressure 

coefficient – ESP

CP156 = (P156*144 –

PINF)/QINF

560 CP157 Model surface pressure 

coefficient – ESP

CP157 = (P157*144 –

PINF)/QINF

561 CP158 Model surface pressure 

coefficient – ESP

CP158 = (P158*144 –

PINF)/QINF

562 CP159 Model surface pressure 

coefficient – ESP

CP159 = (P159*144 –

PINF)/QINF

563 CP160 Model surface pressure 

coefficient – ESP

CP160 = (P160*144 –

PINF)/QINF

564 CP161 Model surface pressure 

coefficient – ESP

CP161 = (P161*144 –

PINF)/QINF

565 CP162 Model surface pressure 

coefficient – ESP

CP162 = (P162*144 –

PINF)/QINF

566 CP163 Model surface pressure 

coefficient – ESP

CP163 = (P163*144 –

PINF)/QINF

567 CP164 Model surface pressure 

coefficient – ESP

CP164 = (P164*144 –

PINF)/QINF

568 CP165 Model surface pressure 

coefficient – ESP

CP165 = (P165*144 –

PINF)/QINF

569 CP166 Model surface pressure 

coefficient – ESP

CP166 = (P166*144 –

PINF)/QINF

570 CP167 Model surface pressure 

coefficient – ESP

CP167 = (P167*144 –

PINF)/QINF

571 CP168 Model surface pressure 

coefficient – ESP

CP168 = (P168*144 –

PINF)/QINF

572 CP169 Model surface pressure 

coefficient – ESP

CP169 = (P169*144 –

PINF)/QINF

573 CP170 Model surface pressure 

coefficient – ESP

CP170 = (P170*144 –

PINF)/QINF

574 CP171 Model surface pressure 

coefficient – ESP

CP171 = (P171*144 –

PINF)/QINF

Table A-2. Continued.

(j) Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

90

# NAME VALUE UNITS DESCRIPTION EQUATION

575 CP172 Model surface pressure 

coefficient – ESP

CP172 = (P172*144 –

PINF)/QINF

576 CP173 Model surface pressure 

coefficient – ESP

CP173 = (P173*144 –

PINF)/QINF

577 CP174 Model surface pressure 

coefficient – ESP

CP174 = (P174*144 –

PINF)/QINF

578 CP175 Model surface pressure 

coefficient – ESP

CP175 = (P175*144 –

PINF)/QINF

579 CP176 Model surface pressure 

coefficient – ESP

CP176 = (P176*144 –

PINF)/QINF

Table A-2. Continued.

(j) Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

91
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

92
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

93
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

94
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

95
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

96
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

97
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

98
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

99
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

100
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

101
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

102
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

103
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

104
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

105
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

106
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

107
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

108
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

109
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

110

A2.0 Photos of Parts and Assembly Taken During Model Acceptance Fit Check 

(6/24/10)

Figure A-3. SRP model sting showing high pressure air supply port.

Figure A-4. ULTEM insulator saddle block.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

111

Figure A-5. Manifold assembly.

Figure A-6. Initial assembly of forebody and manifold.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

112

Figure A-7. Forebody assembly with baseline inserts installed.

Figure A-8. Six of eight baseline and nozzle inserts.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

113

Figure A-9. Instrumented half aft shell.

Figure A-10. Rear cover support plate showing wiring access hole.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

114

Figure A-11. Assembly of sting and rear cover support plate.

Figure A-12. Backside of forebody showing pressure tube port posts and shims 

for inserts.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

115

Figure A-13. Sting assembly with Kulite pressure transducers installed.

Figure A-14. Insulator saddle block with one ESP module attached.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

116

Figure A-15. Installation of the double O-rings for each insert.

Figure A-16. Center plug installation prior to seating the insert past the O-rings.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

117

Figure A-17. All four baseline plug inserts in the proper (seated) position.

Figure A-18. Forebody guide posts used for proper alignment of manifold during 

assembly.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

118

Figure A-19. Installation of bolts that hold forebody in place.

Figure A-20. O-ring between manifold and sting/plenum.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

119

Figure A-21. Installation of bolts that hold manifold to sting.

Figure A-22. Installation of saddle block with one ESP module attached.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

120

Figure A-23. Close-up of a saddle block thermocouple for monitoring ESP 

module temperatures.

Figure A-24. Installation of the aft cover plates.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

121

Figure A-25. View showing model internal volume before installation of pressure 

tubes.

Figure A-26. Close-up showing clearance between ESP module and aft cover 

plate.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

122

Figure A-27. Installation of second aft cover plate.

Figure A-28. Fully assembled model with baseline inserts.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

123

Figure A-29. All four nozzle inserts in the proper (seated) position.

Figure A-30. Assembly of the forebody and manifold with nozzle inserts.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

124

APPENDIX B

TEST DETAILS

This appendix contains details pertaining to the test, including tables of the notional run matrix, 

notional thrust coefficients, Test 11853 chronological run log, pitch sweep, and a statistical 

analysis of the resulting flow conditions.

Table B-1. Notional run matrix.

(a) Baseline: no nozzles test matrix.

# of 

Nozzles

Model Attitude & Location Plenum Conditions Mach Number / PT1 (psf)

Pitch Roll X_Strut Y_Strut CT PTJ TTJ 2.40 3.50 4.60

{deg} {deg} {in} {in} {psia} {R} 779.1 1442.5 2441.3

0 A1 0 40.163 0 0.0 0 0 20, 24 56 111

0 A1 60 40.163 0 0.0 0 0 21, 25 55 110

0 A1 120 40.163 0 0.0 0 0 22 54 109

0 A1 180 40.163 0 0.0 0 0 23 53 108

0 A1 0 25.163 0 0.0 0 0 33 57 104

0 A1 60 25.163 0 0.0 0 0 32 58 105

0 A1 120 25.163 0 0.0 0 0 31 59 106

0 A1 180 25.163 0 0.0 0 0 30 60 107

0 A1 0 50.163 0 0.0 0 0 26 49 112

0 A1 60 50.163 0 0.0 0 0 27 50 113

0 A1 120 50.163 0 0.0 0 0 28 51 114

0 A1 180 50.163 0 0.0 0 0 29 52 115

0 A1 0 40.163 8 0.0 0 0 41 76

0 A1 60 40.163 8 0.0 0 0 40 77

0 A1 120 40.163 8 0.0 0 0 39 78

0 A1 180 40.163 8 0.0 0 0 38 79

0 A1 0 40.163 –8 0.0 0 0 42 75

0 A1 60 40.163 –8 0.0 0 0 43 74

0 A1 120 40.163 –8 0.0 0 0 44 73

0 A1 180 40.163 –8 0.0 0 0 45 70

0 A1 0 25.163 8 0.0 0 0 34

0 A1 60 25.163 8 0.0 0 0 35

0 A1 120 25.163 8 0.0 0 0 36

0 A1 180 25.163 8 0.0 0 0 37

0 A1 0 50.163 –8 0.0 0 0 49

0 A1 60 50.163 –8 0.0 0 0 48

0 A1 120 50.163 –8 0.0 0 0 47
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

125

# of 

Nozzles

Model Attitude & Location Plenum Conditions Mach Number / PT1 (psf)

Pitch Roll X_Strut Y_Strut CT PTJ TTJ 2.40 3.50 4.60

{deg} {deg} {in} {in} {psia} {R} 779.1 1442.5 2441.3

0 A1 180 50.163 –8 0.0 0 0 46

0 A1 0 25.163 –8 0.0 0 0 65 120

0 A1 60 25.163 –8 0.0 0 0 67 121

0 A1 120 25.163 –8 0.0 0 0 68 122

0 A1 180 25.163 –8 0.0 0 0 69 123

0 A1 0 50.163 8 0.0 0 0 83 119

0 A1 60 50.163 8 0.0 0 0 82 118

0 A1 120 50.163 8 0.0 0 0 81 117

0 A1 180 50.163 8 0.0 0 0 80 116

(b) Center nozzle-only test matrix.

# of 

Nozzles

Model Attitude & Location Plenum Conditions Mach Number / PT1 (psf)

Pitch Roll X_Strut Y_Strut CT PTJ TTJ 2.40 3.50 4.60

{deg} {deg} {in} {in} {psia} {R} 779.1 1442.5 2441.3

1 A1 0 40.163 0 0.0 0 0 149 162 174

1 A1 60 40.163 0 0.0 0 0

1 A1 120 40.163 0 0.0 0 0

1 A1 180 40.163 0 0.0 0 0 148 161 173

1 A1 0 40.163 0 0.25 table 640 145 159 171

1 A1 60 40.163 0 0.25 table 640

1 A1 120 40.163 0 0.25 table 640

1 A1 180 40.163 0 0.25 table 640 146 160 172

1 A1 0 40.163 0 0.5 table 640 144 157 170

1 A1 60 40.163 0 0.5 table 640

1 A1 120 40.163 0 0.5 table 640

1 A1 180 40.163 0 0.5 table 640 143 156 169

1 A1 0 40.163 0 1.0 table 640 140 154 167

1 A1 60 40.163 0 1.0 table 640

1 A1 120 40.163 0 1.0 table 640

1 A1 180 40.163 0 1.0 table 640 139 155 168

1 A1 0 40.163 0 2.0 table 640 141 153 166

1 A1 60 40.163 0 2.0 table 640

1 A1 120 40.163 0 2.0 table 640

1 A1 180 40.163 0 2.0 table 640 142 152 165

Table B-1. Continued.

(a) Concluded

(a) Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

126

# of 

Nozzles

Model Attitude & Location Plenum Conditions Mach Number / PT1 (psf)

Pitch Roll X_Strut Y_Strut CT PTJ TTJ 2.40 3.50 4.60

{deg} {deg} {in} {in} {psia} {R} 779.1 1442.5 2441.3

1 A1 0 40.163 0 3.0 table 640 137 150 163

1 A1 60 40.163 0 3.0 table 640

1 A1 120 40.163 0 3.0 table 640

1 A1 180 40.163 0 3.0 table 640 138 151 164

1 A1 0 25.163 0 0.5 table 640

1 A1 60 25.163 0 0.5 table 640

1 A1 120 25.163 0 0.5 table 640

1 A1 180 25.163 0 0.5 table 640

1 A1 0 50.163 0 0.5 table 640

1 A1 60 50.163 0 0.5 table 640

1 A1 120 50.163 0 0.5 table 640

1 A1 180 50.163 0 0.5 table 640

1 A1 0 25.163 0 1.0 table 640

1 A1 60 25.163 0 1.0 table 640

1 A1 120 25.163 0 1.0 table 640

1 A1 180 25.163 0 1.0 table 640

1 A1 0 50.163 0 1.0 table 640

1 A1 60 50.163 0 1.0 table 640

1 A1 120 50.163 0 1.0 table 640

1 A1 180 50.163 0 1.0 table 640

1 A1 0 25.163 4 1.0 table 640

1 A1 60 25.163 4 1.0 table 640

1 A1 120 25.163 4 1.0 table 640

1 A1 180 25.163 4 1.0 table 640

1 A1 0 25.163 –4 1.0 table 640

1 A1 60 25.163 –4 1.0 table 640

1 A1 120 25.163 –4 1.0 table 640

1 A1 180 25.163 –4 1.0 table 640

1 A1 0 40.163 0 3.0 table 640

1 A1 60 40.163 0 3.0 table 640

1 A1 120 40.163 0 3.0 table 640

1 A1 180 40.163 0 3.0 table 640

1 A1 0 40.163 0 5.0 table 640

1 A1 60 40.163 0 5.0 table 640

1 A1 120 40.163 0 5.0 table 640

1 A1 180 40.163 0 5.0 table 640

Table B-1. Continued.

(b) Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

127

Table B-1. Continued.

(c) Tri-nozzle test matrix.

# of 

Nozzles

Model Attitude & Location Plenum 

Conditions Mach Number / PT1 (psf)

Pitch Roll X_Strut Y_Strut CT PTJ TTJ 2.40 3.50 4.60

{deg} {deg} {in} {in} {psia} {R} 779.1 1442.5 2441.3

3 A1 0 40.163 0 0.0 0 0 180 184 258

3 A1 60 40.163 0 0.0 0 0 183 185 259

3 A1 120 40.163 0 0.0 0 0 182 186 260

3 A1 180 40.163 0 0.0 0 0 181 187 261

3 A1 0 40.163 0 0.25 table 640 221 241 257

3 A1 60 40.163 0 0.25 table 640

3 A1 120 40.163 0 0.25 table 640

3 A1 180 40.163 0 0.25 table 640

3 A1 0 40.163 0 0.5 table 640 217 240,266 253

3 A1 60 40.163 0 0.5 table 640 218 239 254

3 A1 120 40.163 0 0.5 table 640 219 238 255

3 A1 180 40.163 0 0.5 table 640 220 237 256

3 A1 0 40.163 0 1.0 table 640 198 230,234,265 252

3 A1 60 40.163 0 1.0 table 640 199 233 251

3 A1 120 40.163 0 1.0 table 640 200 235 250

3 A1 180 40.163 0 1.0 table 640 201 236 249

3 A1 0 40.163 0 2.0 table 640 197 229 242,247

3 A1 60 40.163 0 2.0 table 640 196 228 243

3 A1 120 40.163 0 2.0 table 640 195 227 244

3 A1 180 40.163 0 2.0 table 640 194 226 245,248

3 A1 0 40.163 0 3.0 table 640 190 222 211,262

3 A1 60 40.163 0 3.0 table 640 191 223 212

3 A1 120 40.163 0 3.0 table 640 192 224 213

3 A1 180 40.163 0 3.0 table 640 193 225 214,263

3 A1 0 25.163 0 0.5 table 640

3 A1 60 25.163 0 0.5 table 640

3 A1 120 25.163 0 0.5 table 640

3 A1 180 25.163 0 0.5 table 640

3 A1 0 50.163 0 0.5 table 640

3 A1 60 50.163 0 0.5 table 640

3 A1 120 50.163 0 0.5 table 640

3 A1 180 50.163 0 0.5 table 640

3 A1 0 25.163 0 1.0 table 640
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

128

# of 

Nozzles

Model Attitude & Location Plenum 

Conditions Mach Number / PT1 (psf)

Pitch Roll X_Strut Y_Strut CT PTJ TTJ 2.40 3.50 4.60

{deg} {deg} {in} {in} {psia} {R} 779.1 1442.5 2441.3

3 A1 60 25.163 0 1.0 table 640

3 A1 120 25.163 0 1.0 table 640

3 A1 180 25.163 0 1.0 table 640

3 A1 0 50.163 0 1.0 table 640

3 A1 60 50.163 0 1.0 table 640

3 A1 120 50.163 0 1.0 table 640

3 A1 180 50.163 0 1.0 table 640

3 A1 0 25.163 4 1.0 table 640

3 A1 60 25.163 4 1.0 table 640

3 A1 120 25.163 4 1.0 table 640

3 A1 180 25.163 4 1.0 table 640

3 A1 0 25.163 –4 1.0 table 640

3 A1 60 25.163 –4 1.0 table 640

3 A1 120 25.163 –4 1.0 table 640

3 A1 180 25.163 –4 1.0 table 640

3 A1 0 40.163 0 3.0 table 640

3 A1 60 40.163 0 3.0 table 640

3 A1 120 40.163 0 3.0 table 640

3 A1 180 40.163 0 3.0 table 640

3 A1 0 40.163 0 5.0 table 640

3 A1 60 40.163 0 5.0 table 640

3 A1 120 40.163 0 5.0 table 640

3 A1 180 40.163 0 5.0 table 640

(d) Quad-nozzle test matrix.

# of 

Nozzles

Model Attitude & Location Plenum Conditions Mach Number / PT1 (psf)

Pitch Roll X_Strut Y_Strut CT PTJ TTJ 2.40 3.50 4.60

{deg} {deg} {in} {in} {psia} {R} 779.1 1442.5 2441.3

4 A1 0 40.163 0 0.0 0 0

4 A1 60 40.163 0 0.0 0 0

4 A1 120 40.163 0 0.0 0 0

4 A1 180 40.163 0 0.0 0 0

4 A1 0 40.163 0 0.25 table 640

Table B-1. Continued.

(c) Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

129

# of 

Nozzles

Model Attitude & Location Plenum Conditions Mach Number / PT1 (psf)

Pitch Roll X_Strut Y_Strut CT PTJ TTJ 2.40 3.50 4.60

{deg} {deg} {in} {in} {psia} {R} 779.1 1442.5 2441.3

4 A1 60 40.163 0 0.25 table 640

4 A1 120 40.163 0 0.25 table 640

4 A1 180 40.163 0 0.25 table 640

4 A1 0 40.163 0 0.5 table 640

4 A1 60 40.163 0 0.5 table 640

4 A1 120 40.163 0 0.5 table 640

4 A1 180 40.163 0 0.5 table 640

4 A1 0 40.163 0 1.0 table 640 296 305 315

4 A1 60 40.163 0 1.0 table 640 295 304 314

4 A1 120 40.163 0 1.0 table 640 294 303 313

4 A1 180 40.163 0 1.0 table 640 293 302 312

4 A1 0 40.163 0 2.0 table 640 288 298 307

4 A1 60 40.163 0 2.0 table 640 289 299 309

4 A1 120 40.163 0 2.0 table 640 290 300 310

4 A1 180 40.163 0 2.0 table 640 291 301 311

4 A1 0 40.163 0 3.0 table 640

4 A1 60 40.163 0 3.0 table 640

4 A1 120 40.163 0 3.0 table 640

4 A1 180 40.163 0 3.0 table 640

(e) Baseline: repeat at the end of the test.

# of 

Nozzles

Model Attitude & Location Plenum Conditions Mach Number / PT1 (psf)

Pitch Roll X_Strut Y_Strut CT PTJ TTJ 2.40 3.50 4.60

{deg} {deg} {in} {in} {psia} {R} 779.1 1442.5 2441.3

0 A1 0 40.163 0 0.0 0 0 271 279 280

0 A1 60 40.163 0 0.0 0 0 272 278 281

0 A1 120 40.163 0 0.0 0 0 273 277 282

0 A1 180 40.163 0 0.0 0 0 274 276 283

0 A1 0 25.163 –8 0.0 0 0

0 A1 60 25.163 –8 0.0 0 0

0 A1 120 25.163 –8 0.0 0 0

0 A1 180 25.163 –8 0.0 0 0

0 A1 0 50.163 8 0.0 0 0

0 A1 60 50.163 8 0.0 0 0

0 A1 120 50.163 8 0.0 0 0

0 A1 180 50.163 8 0.0 0 0

Table B-1. Continued

(d) Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

130

Table B-1. Continued.

(f) Tri-nozzle repeat at the end of the test.

# of 

Nozzles

Model Attitude & Location Plenum Conditions Mach Number / PT1 (psf)

Pitch Roll X_Strut Y_Strut CT PTJ TTJ 2.40 3.50 4.60

{deg} {deg} {in} {in} {psia} {R} 779.1 1442.5 2441.3

3 A1 0 40.163 0 0.5 table 640

3 A1 60 40.163 0 0.5 table 640

3 A1 120 40.163 0 0.5 table 640

3 A1 180 40.163 0 0.5 table 640

3 A1 0 40.163 0 1.0 table 640

3 A1 60 40.163 0 1.0 table 640

3 A1 120 40.163 0 1.0 table 640

3 A1 180 40.163 0 1.0 table 640

3 A1 0 40.163 0 2.0 table 640

3 A1 60 40.163 0 2.0 table 640

3 A1 120 40.163 0 2.0 table 640

3 A1 180 40.163 0 2.0 table 640

Table B-2. Notational trust coefficients.

(a) Center nozzle.

MACH 2.4 3.5 4.6

CT PTJ, psia (TTJ = 180°F)

0.25 96.97 70.48 74.75

0.5 193.94 140.95 149.50

1 387.89 281.90 299.00

2 775.77 563.80 598.00

3 1163.66 845.70 897.01

4 1551.55 1127.61 1196.01

5 1939.44 1409.51 1495.01

6 2327.32 1691.41 1794.01

7 2715.21 1973.31 2093.01

8 3103.10 2255.21 2392.01

9 3490.99 2537.11 2691.02

10 3878.87 2819.01 2990.02
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

131

Table B-2. Concluded.

(b) Tri-nozzle.

MACH 2.4 3.5 4.6

CT PTJ, psia (TTJ = 180°F)

0.25 32.32 23.49 24.92

0.5 64.65 46.98 49.83

1 129.30 93.97 99.67

2 258.59 187.93 199.33

3 387.89 281.90 299.00

4 517.18 375.87 398.67

5 646.48 469.84 498.34

6 775.77 563.80 598.00

7 905.07 657.77 697.67

8 1034.37 751.74 797.34

9 1163.66 845.70 897.01

10 1292.96 939.67 996.67

(c) Quad-nozzle.

MACH 2.4 3.5 4.6

CT PTJ, psia (TTJ = 180°F)

0.25 24.24 17.62 18.69

0.5 48.49 35.24 37.38

1 96.97 70.48 74.75

2 193.94 140.95 149.50

3 290.92 211.43 224.25

4 387.89 281.90 299.00

5 484.86 352.38 373.75

6 581.83 422.85 448.50

7 678.80 493.33 523.25

8 775.77 563.80 598.00

9 872.75 634.28 672.75

10 969.72 704.75 747.50
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

132

Table B-3. Chronological run log.

RUN INFORMATION MODEL ATTITUDE & LOCATION RUN-AVERAGED FLOW CONDITIONS NOZZLE EXIT CONDITIONS

DATE TIME RUN POINT

Key # 

NOZ

PITCH ROLL X_STRUT Y_STRUT PTINF TTINF MACH REINF PINF TINF RHOINF QINF DEWPT PTJ TTJ WJ CT

2010 START END {deg} {deg} {in} {in} {psf} {R} {1/ft} {psf} {R} {slug/ft^3} {psf} {deg F} {psia} {R} {lbm/sec}

7/13 13:44 9 467 467 4 0 0.006 0.03 5.01 0.00 2115.71 539.47 0.0 0.00E+00 2115.7 539.5 2.28E–03 0.00 70.16 0.00 0.00 0.000 0.000

7/13 15:11 10 468 468 2 0 –0.005 0.01 25.72 0.00 2115.07 539.62 0.0 0.00E+00 2115.1 539.6 2.28E–03 0.00 70.16 0.00 0.00 0.000 0.000

7/13 17:19 10 469 477 1 0 B4–A1 0.01 40.16 0.00 778.31 595.24 2.4 9.98E+05 53.2 276.6 1.12E–04 214.65 –18.61 0.00 0.00 0.000 0.000

7/13 17:34 11 478 486 1 0 B4–A1 59.98 40.16 0.00 778.00 594.68 2.4 9.99E+05 53.2 276.3 1.12E–04 214.56 –13.73 0.00 0.00 0.000 0.000

7/13 17:43 11 487 488 3 0 –0.079 0.01 40.16 0.00 196.12 579.73 0.0 0.00E+00 196.1 579.7 2.90E–05 0.00 –13.59 0.00 0.00 0.000 0.000

7/13 17:47 11 489 489 3 0 –0.076 0.01 40.16 0.00 2108.16 610.54 0.0 0.00E+00 2108.2 610.5 2.01E–03 0.00 –29.68 0.00 0.00 0.000 0.000

7/14 7:44 12 490 490 2 0 –0.079 0.01 40.16 0.00 2117.23 549.43 0.0 0.00E+00 2117.2 549.4 2.24E–03 0.00 70.33 0.00 0.00 0.000 0.000

7/14 7:59 12 491 492 2 0 –0.072 0.01 40.16 0.00 380.37 522.86 0.0 0.00E+00 380.4 522.9 4.24E–04 0.00 –14.35 0.00 0.00 0.000 0.000

7/14 9:39 13 493 504 1 0 B4–A1 0.03 25.16 0.03 777.56 594.72 2.4 9.99E+05 53.2 276.4 1.12E–04 214.44 –23.89 16.26 580.89 0.000 0.000

7/14 9:49 14 505 516 1 0 B4–A1 59.71 25.16 –0.03 777.37 594.62 2.4 9.99E+05 53.2 276.3 1.12E–04 214.39 –24.07 16.29 580.78 0.000 0.000

7/14 9:52 15 517 517 5 0 B4–A1 119.90 25.16 0.00 776.95 594.67 2.4 9.98E+05 53.1 276.3 1.12E–04 214.27 –24.09 0.00 0.00 0.000 0.000

7/14 10:05 16 518 527 1 0 B4–A1 0.05 25.16 0.00 777.90 594.75 2.4 9.99E+05 53.2 276.4 1.12E–04 214.53 –24.18 16.28 580.86 0.000 0.000

7/14 10:11 17 528 536 1 0 B4–A1 59.53 25.16 0.00 777.38 594.45 2.4 9.99E+05 53.2 276.2 1.12E–04 214.39 –24.24 16.29 580.84 0.000 0.000

7/14 10:16 18 537 545 1 0 B4–A1 120.30 25.16 0.00 777.50 594.80 2.4 9.99E+05 53.2 276.4 1.12E–04 214.42 –24.29 16.32 580.90 0.000 0.000

7/14 10:21 19 546 554 1 0 B4–A1 179.92 25.16 0.00 777.48 594.73 2.4 9.99E+05 53.2 276.4 1.12E–04 214.42 –24.36 16.35 580.97 0.000 0.000

7/14 10:50 20 557 565 1 0 B4–A1 0.01 39.93 0.00 777.60 594.84 2.4 9.99E+05 53.2 276.4 1.12E–04 214.45 –22.45 16.28 580.53 0.000 0.000

7/14 11:28 21 566 574 1 0 B4–A1 59.53 39.93 0.00 777.50 594.33 2.4 1.00E+06 53.2 276.2 1.12E–04 214.42 –24.53 16.43 582.97 0.000 0.000

7/14 11:36 22 575 583 1 0 B4–A1 120.41 39.93 0.00 777.43 594.76 2.4 9.99E+05 53.2 276.4 1.12E–04 214.41 –24.45 16.43 582.62 0.000 0.000

7/14 11:42 23 584 592 1 0 B4–A1 179.99 39.93 0.00 777.70 594.74 2.4 9.99E+05 53.2 276.4 1.12E–04 214.48 –24.46 16.43 582.40 0.000 0.000

7/14 11:47 24 593 601 1 0 B4–A1 0.01 39.93 0.00 777.60 594.52 2.4 9.99E+05 53.2 276.3 1.12E–04 214.45 –24.53 16.38 582.08 0.000 0.000

7/14 11:53 25 602 610 1 0 B4–A1 59.67 39.93 0.00 777.46 594.79 2.4 9.99E+05 53.2 276.4 1.12E–04 214.41 –24.62 16.38 581.99 0.000 0.000

7/14 12:03 26 611 619 1 0 B4–A1 0.03 50.17 0.00 777.38 594.50 2.4 9.99E+05 53.2 276.3 1.12E–04 214.39 –24.70 16.39 582.28 0.000 0.000

7/14 12:08 27 620 628 1 0 B4–A1 59.67 50.17 0.00 777.50 594.75 2.4 9.99E+05 53.2 276.4 1.12E–04 214.42 –24.73 16.39 582.26 0.000 0.000

7/14 12:13 28 629 637 1 0 B4–A1 120.47 50.17 0.00 777.48 594.79 2.4 9.99E+05 53.2 276.4 1.12E–04 214.42 –24.72 16.41 582.25 0.000 0.000

7/14 12:19 29 638 646 1 0 B4–A1 179.91 50.17 0.00 776.98 594.37 2.4 9.99E+05 53.1 276.2 1.12E–04 214.28 –24.71 16.42 582.19 0.000 0.000

7/14 12:27 30 647 655 1 0 B4–A1 179.91 25.18 0.00 777.46 594.27 2.4 1.00E+06 53.2 276.1 1.12E–04 214.41 –24.83 16.40 581.99 0.000 0.000

7/14 12:32 31 656 664 1 0 B4–A1 120.33 25.18 0.00 777.74 595.02 2.4 9.98E+05 53.2 276.5 1.12E–04 214.49 –24.82 16.39 581.77 0.000 0.000

7/14 12:37 32 665 673 1 0 B4–A1 59.57 25.18 0.00 777.58 594.37 2.4 1.00E+06 53.2 276.2 1.12E–04 214.44 –24.77 16.37 581.80 0.000 0.000

7/14 12:44 33 674 682 1 0 B4–A1 0.05 25.18 0.00 777.46 594.75 2.4 9.99E+05 53.2 276.4 1.12E–04 214.41 –24.71 16.36 581.86 0.000 0.000

7/14 12:58 34 683 691 1 0 B4–A1 0.05 25.18 7.99 777.72 594.78 2.4 9.99E+05 53.2 276.4 1.12E–04 214.48 –24.71 16.38 582.35 0.000 0.000

7/14 13:04 35 692 700 1 0 B4–A1 59.67 25.18 7.99 777.46 594.58 2.4 9.99E+05 53.2 276.3 1.12E–04 214.41 –24.71 16.39 582.11 0.000 0.000
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

133

RUN INFORMATION MODEL ATTITUDE & LOCATION RUN-AVERAGED FLOW CONDITIONS NOZZLE EXIT CONDITIONS

DATE TIME RUN POINT

Key # 

NOZ

PITCH ROLL X_STRUT Y_STRUT PTINF TTINF MACH REINF PINF TINF RHOINF QINF DEWPT PTJ TTJ WJ CT

2010 START END {deg} {deg} {in} {in} {psf} {R} {1/ft} {psf} {R} {slug/ft^3} {psf} {deg F} {psia} {R} {lbm/sec}

7/14 13:09 36 701 709 1 0 B4–A1 120.31 25.18 7.99 777.46 594.52 2.4 9.99E+05 53.2 276.3 1.12E–04 214.41 –24.71 16.40 581.96 0.000 0.000

7/14 13:14 37 710 718 1 0 B4–A1 179.95 25.18 7.99 777.55 594.67 2.4 9.99E+05 53.2 276.3 1.12E–04 214.44 –24.71 16.40 581.80 0.000 0.000

7/14 13:22 38 719 727 1 0 B4–A1 179.95 40.19 7.99 777.72 594.74 2.4 9.99E+05 53.2 276.4 1.12E–04 214.48 –24.62 16.40 581.86 0.000 0.000

7/14 13:27 39 728 736 1 0 B4–A1 120.31 40.19 7.99 777.53 594.51 2.4 9.99E+05 53.2 276.3 1.12E–04 214.43 –24.54 16.40 581.86 0.000 0.000

7/14 13:32 40 737 745 1 0 B4–A1 59.57 40.19 7.99 777.36 594.53 2.4 9.99E+05 53.2 276.3 1.12E–04 214.39 –24.47 16.38 581.83 0.000 0.000

7/14 13:38 41 746 754 1 0 B4–A1 –0.05 40.19 7.99 777.65 594.63 2.4 9.99E+05 53.2 276.3 1.12E–04 214.46 –24.42 16.36 581.76 0.000 0.000

7/14 13:51 42 755 763 1 0 B4–A1 –0.05 40.19 –8.00 777.67 595.13 2.4 9.98E+05 53.2 276.5 1.12E–04 214.47 –23.39 16.40 582.34 0.000 0.000

7/14 14:05 43 764 772 1 0 B4–A1 59.51 40.19 –8.00 777.02 595.71 2.4 9.96E+05 53.1 276.8 1.12E–04 214.29 –18.12 16.43 582.91 0.000 0.000

7/14 14:10 44 773 781 1 0 B4–A1 120.31 40.19 –8.00 777.41 594.30 2.4 1.00E+06 53.2 276.2 1.12E–04 214.40 –18.29 16.43 582.41 0.000 0.000

7/14 14:15 45 782 790 1 0 B4–A1 179.95 40.19 –8.00 777.55 594.79 2.4 9.99E+05 53.2 276.4 1.12E–04 214.44 –18.97 16.44 582.30 0.000 0.000

7/14 14:24 46 791 799 1 0 B4–A1 179.95 50.16 –8.00 777.41 594.50 2.4 9.99E+05 53.2 276.3 1.12E–04 214.40 –25.57 16.42 582.08 0.000 0.000

7/14 14:29 47 800 808 1 0 B4–A1 120.33 50.16 –8.00 777.60 594.95 2.4 9.98E+05 53.2 276.5 1.12E–04 214.45 –25.30 16.42 582.00 0.000 0.000

7/14 14:34 48 809 817 1 0 B4–A1 59.57 50.16 –8.00 777.55 594.39 2.4 1.00E+06 53.2 276.2 1.12E–04 214.44 –25.45 16.40 582.16 0.000 0.000

7/14 14:39 49 818 826 1 0 B4–A1 –0.04 50.16 –8.00 777.48 595.01 2.4 9.98E+05 53.2 276.5 1.12E–04 214.42 –25.19 16.40 582.15 0.000 0.000

7/14 15:13 49 827 835 1 0 B4–A1 –0.04 50.16 –8.00 777.48 595.01 2.4 9.98E+05 53.2 276.5 1.12E–04 214.42 –25.19 16.40 582.15 0.000 0.000

7/14 15:19 50 836 844 1 0 B4–A1 59.61 50.16 0.00 1386.36 594.67 3.5 9.99E+05 18.2 172.4 6.14E–05 155.86 –16.04 16.34 580.96 0.000 0.000

7/14 15:33 51 847 855 1 0 B4–A1 120.35 50.16 0.00 1386.55 595.15 3.5 9.98E+05 18.2 172.5 6.14E–05 155.88 –13.60 16.31 579.80 0.000 0.000

7/14 15:38 52 856 864 1 0 B4–A1 179.99 50.16 0.00 1387.18 595.56 3.5 9.98E+05 18.2 172.6 6.14E–05 155.95 –12.40 16.31 579.53 0.000 0.000

7/14 15:50 53 865 873 1 0 B4–A1 179.99 40.17 0.00 1386.19 594.72 3.5 9.99E+05 18.2 172.4 6.14E–05 155.84 –20.34 16.26 578.99 0.000 0.000

7/14 16:20 54 874 882 1 0 B4–A1 120.47 40.17 0.00 1386.60 594.33 3.5 1.00E+06 18.2 172.3 6.15E–05 155.89 –22.28 16.20 578.45 0.000 0.000

7/14 16:25 55 883 891 1 0 B4–A1 59.57 40.17 0.00 1386.48 594.94 3.5 9.99E+05 18.2 172.4 6.14E–05 155.88 –22.02 16.17 578.16 0.000 0.000

7/14 16:30 56 892 900 1 0 B4–A1 –0.07 40.17 0.00 1386.65 595.21 3.5 9.98E+05 18.2 172.5 6.14E–05 155.90 –21.97 16.14 577.95 0.000 0.000

7/14 16:39 57 901 909 1 0 B4–A1 –0.07 25.16 0.00 1385.88 594.07 3.5 1.00E+06 18.2 172.2 6.15E–05 155.81 –19.64 16.12 577.70 0.000 0.000

7/14 16:44 58 910 918 1 0 B4–A1 59.63 25.16 0.00 1386.58 594.44 3.5 1.00E+06 18.2 172.3 6.15E–05 155.89 –19.46 16.11 577.40 0.000 0.000

7/14 16:49 59 919 927 1 0 B4–A1 120.47 25.16 0.00 1386.65 594.26 3.5 1.00E+06 18.2 172.2 6.15E–05 155.90 –19.79 16.14 577.35 0.000 0.000

7/14 16:55 60 928 936 1 0 B4–A1 179.95 25.16 0.00 1386.24 594.75 3.5 9.99E+05 18.2 172.4 6.14E–05 155.85 –19.45 16.16 577.23 0.000 0.000

7/14 17:02 61 937 939 3 0 0.031 179.95 25.16 0.00 193.10 585.20 0.0 0.00E+00 193.1 585.2 1.92E–04 0.00 –14.80 0.00 0.00 0.000 0.000

7/14 17:06 61 940 940 3 0 0.026 179.95 25.16 0.00 2117.44 614.60 0.0 0.00E+00 2117.4 614.6 2.01E–04 0.00 –14.72 0.00 0.00 0.000 0.000

7/15 7:13 64 941 941 2 0 0.014 179.95 25.16 0.00 2125.22 560.76 0.0 0.00E+00 2125.2 560.8 2.21E–03 0.00 70.17 0.00 0.00 0.000 0.000

7/15 7:52 64 942 943 2 0 0.016 179.95 25.16 0.00 365.58 538.63 0.0 0.00E+00 365.6 538.6 3.95E–04 0.00 38.48 0.00 0.00 0.000 0.000

7/15 8:55 65 944 952 1 0 B4–A1 –0.01 25.16 –8.00 1387.13 593.83 3.5 1.00E+06 18.2 172.1 6.16E–05 155.95 –24.87 –3.13 572.24 0.000 0.000

7/15 8:59 66 953 959 5 0 B4–A1 60.06 25.16 –8.00 1386.93 595.23 3.5 9.98E+05 18.2 172.5 6.13E–05 155.93 –17.72 0.00 0.00 0.000 0.000

Table B-3. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

134

RUN INFORMATION MODEL ATTITUDE & LOCATION RUN-AVERAGED FLOW CONDITIONS NOZZLE EXIT CONDITIONS

DATE TIME RUN POINT

Key # 

NOZ

PITCH ROLL X_STRUT Y_STRUT PTINF TTINF MACH REINF PINF TINF RHOINF QINF DEWPT PTJ TTJ WJ CT

2010 START END {deg} {deg} {in} {in} {psf} {R} {1/ft} {psf} {R} {slug/ft^3} {psf} {deg F} {psia} {R} {lbm/sec}

7/15 11:19 67 960 968 1 0 B4–A1 59.65 25.16 –8.00 1386.14 593.81 3.5 1.00E+06 18.2 172.1 6.15E–05 155.84 –24.22 –2.76 577.14 0.000 0.000

7/15 11:25 68 969 977 1 0 B4–A1 120.37 25.16 –8.00 1387.34 595.35 3.5 9.98E+05 18.2 172.6 6.14E–05 155.97 –23.69 –2.74 576.94 0.000 0.000

7/15 11:37 69 978 986 1 0 B4–A1 179.95 25.16 –8.00 1387.68 595.31 3.5 9.99E+05 18.2 172.6 6.14E–05 156.01 –23.85 –2.76 576.50 0.000 0.000

7/15 11:53 70 987 995 1 0 B4–A1 179.95 40.16 –8.00 1385.21 594.81 3.5 9.98E+05 18.2 172.4 6.14E–05 155.73 –22.63 –2.77 575.98 0.000 0.000

7/15 12:31 71 996 997 3 0 0.024 179.95 40.16 –8.00 184.57 584.11 0.0 0.00E+00 184.6 584.1 1.84E–04 0.00 –0.36 0.00 0.00 0.000 0.000

7/15 12:35 71 998 998 3 0 0.02 179.95 40.16 –8.00 2124.14 615.72 0.0 0.00E+00 2124.1 615.7 2.01E–03 0.00 –19.62 0.00 0.00 0.000 0.000

7/15 14:40 72 999 1000 2 0 0.236 179.95 41.22 –8.00 399.49 536.57 0.0 0.00E+00 399.5 536.6 4.34E–04 0.00 72.88 0.00 0.00 0.000 0.000

7/15 15:07 73 1001 1009 1 0 B4–A1 120.33 40.18 –8.00 1386.48 595.01 3.5 9.99E+05 18.2 172.5 6.14E–05 155.88 52.08 –3.13 571.26 0.000 0.000

7/15 15:12 74 1010 1018 1 0 B4–A1 59.61 40.18 –8.00 1386.19 594.63 3.5 9.99E+05 18.2 172.4 6.14E–05 155.84 –20.67 –3.11 571.93 0.000 0.000

7/15 15:17 75 1019 1027 1 0 B4–A1 0.03 40.18 –8.00 1386.29 594.87 3.5 9.99E+05 18.2 172.4 6.14E–05 155.86 –20.66 –3.08 572.50 0.000 0.000

7/15 15:27 76 1028 1036 1 0 B4–A1 0.03 40.18 7.99 1386.43 594.64 3.5 1.00E+06 18.2 172.4 6.14E–05 155.87 –23.11 –3.00 573.61 0.000 0.000

7/15 15:33 77 1037 1045 1 0 B4–A1 59.57 40.16 7.99 1386.67 594.55 3.5 1.00E+06 18.2 172.3 6.15E–05 155.90 –22.94 –2.97 573.96 0.000 0.000

7/15 15:38 78 1046 1054 1 0 B4–A1 120.33 40.16 7.95 1387.20 595.03 3.5 9.99E+05 18.2 172.5 6.14E–05 155.96 –23.00 –2.91 574.21 0.000 0.000

7/15 15:45 79 1055 1063 1 0 B4–A1 –179.99 40.16 7.95 1387.03 594.69 3.5 1.00E+06 18.2 172.4 6.15E–05 155.94 –22.39 –2.88 574.51 0.000 0.000

7/15 16:09 80 1064 1072 1 0 B4–A1 –179.99 50.15 7.95 1386.98 595.13 3.5 9.99E+05 18.2 172.5 6.14E–05 155.93 –20.60 –2.85 575.16 0.000 0.000

7/15 16:15 81 1073 1081 1 0 B4–A1 120.33 50.15 7.95 1385.47 594.15 3.5 1.00E+06 18.2 172.2 6.14E–05 155.76 –20.93 –2.82 575.56 0.000 0.000

7/15 16:20 82 1082 1090 1 0 B4–A1 59.59 50.15 7.95 1386.00 594.62 3.5 9.99E+05 18.2 172.4 6.14E–05 155.82 –20.88 –2.86 575.54 0.000 0.000

7/15 16:25 83 1091 1099 1 0 B4–A1 0.01 50.15 7.95 1386.05 594.78 3.5 9.99E+05 18.2 172.4 6.14E–05 155.83 –20.85 –2.87 575.62 0.000 0.000

7/15 16:32 84 1100 1101 3 0 –0.091 0.01 50.15 0.00 192.13 583.61 0.0 0.00E+00 192.1 583.6 1.92E+01 0.00 –21.95 0.00 0.00 0.000 0.000

7/16 6:52 85 1102 1102 2 0 –0.1 0.01 25.17 0.00 2124.57 560.47 0.0 0.00E+00 2124.6 560.5 2.21E–03 0.00 69.44 0.00 0.00 0.000 0.000

7/16 7:54 85 1103 1104 2 0 –0.1 0.01 25.17 0.00 318.06 554.58 0.0 0.00E+00 318.1 554.6 3.34E–04 0.00 –16.36 0.00 0.00 0.000 0.000

7/16 9:40 86 1105 1113 1 0 B4–A1 0.01 25.17 0.00 2600.06 610.78 4.6 1.06E+06 7.9 116.7 3.96E–05 117.56 –13.33 –2.77 578.16 0.000 0.000

7/16 9:49 87 1114 1122 1 0 B4–A1 59.63 25.17 0.00 2599.68 610.27 4.6 1.06E+06 7.9 116.6 3.96E–05 117.54 –13.33 –2.70 579.06 0.000 0.000

7/16 9:55 88 1123 1131 1 0 B4–A1 120.31 25.17 0.00 2599.73 610.22 4.6 1.06E+06 7.9 116.6 3.96E–05 117.55 –17.12 –2.63 579.56 0.000 0.000

7/16 10:00 89 1132 1140 1 0 B4–A1 179.91 25.17 0.00 2599.94 610.12 4.6 1.06E+06 7.9 116.6 3.96E–05 117.55 –19.18 –2.57 580.05 0.000 0.000

7/16 10:06 90 1141 1149 1 0 B4–A1 0.01 40.15 0.00 2599.51 610.16 4.6 1.06E+06 7.9 116.6 3.96E–05 117.54 –19.11 –2.62 580.52 0.000 0.000

7/16 10:12 91 1150 1158 1 0 B4–A1 59.59 40.18 0.00 2599.82 609.99 4.6 1.07E+06 7.9 116.6 3.97E–05 117.55 –19.12 –2.58 580.90 0.000 0.000

7/16 10:17 92 1159 1167 1 0 B4–A1 120.33 40.18 0.00 2599.56 610.06 4.6 1.06E+06 7.9 116.6 3.96E–05 117.54 –19.16 –2.54 581.18 0.000 0.000

7/16 10:22 93 1168 1176 1 0 B4–A1 179.91 40.18 0.00 2599.92 609.97 4.6 1.07E+06 7.9 116.6 3.97E–05 117.55 –19.22 –2.50 581.54 0.000 0.000

7/16 10:27 94 1177 1185 1 0 B4–A1 179.91 50.14 0.00 2599.54 610.02 4.6 1.06E+06 7.9 116.6 3.96E–05 117.54 –19.22 –2.48 581.87 0.000 0.000

7/16 10:32 95 1186 1194 1 0 B4–A1 120.31 50.14 0.00 2599.85 609.89 4.6 1.07E+06 7.9 116.6 3.97E–05 117.55 –19.23 –2.48 582.13 0.000 0.000

7/16 10:37 96 1195 1203 1 0 B4–A1 59.55 50.14 0.00 2599.22 609.82 4.6 1.07E+06 7.9 116.6 3.97E–05 117.52 –19.23 –2.50 582.37 0.000 0.000

Table B-3. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

135

RUN INFORMATION MODEL ATTITUDE & LOCATION RUN-AVERAGED FLOW CONDITIONS NOZZLE EXIT CONDITIONS

DATE TIME RUN POINT

Key # 

NOZ

PITCH ROLL X_STRUT Y_STRUT PTINF TTINF MACH REINF PINF TINF RHOINF QINF DEWPT PTJ TTJ WJ CT

2010 START END {deg} {deg} {in} {in} {psf} {R} {1/ft} {psf} {R} {slug/ft^3} {psf} {deg F} {psia} {R} {lbm/sec}

7/16 10:43 97 1204 1212 1 0 B4–A1 –0.07 50.14 0.00 2599.54 609.84 4. 6 1.07E+06 7.9 116.6 3.97E–05 117.54 –19.19 –2.50 582.56 0.000 0.000

7/16 11:17 98 1213 1221 1 0 B4–A1 –0.07 50.14 7.99 2599.73 609.53 4.6 1.07E+06 7.9 116.5 3.97E–05 117.55 –18.64 –2.38 584.64 0.000 0.000

7/16 11:24 99 1222 1231 1 0 B4–A1 59.51 50.14 7.99 2599.66 609.77 4.6 1.07E+06 7.9 116.5 3.97E–05 117.54 –17.99 –2.36 584.90 0.000 0.000

7/16 11:32 100 1232 1240 1 0 B4–A1 120.42 50.14 7.99 2599.80 609.55 4.6 1.07E+06 7.9 116.5 3.97E–05 117.55 –16.93 –2.32 585.11 0.000 0.000

7/16 11:36 101 1241 1244 1 0 B4–A1 179.97 50.14 7.99 2600.26 609.52 4.6 1.07E+06 7.9 116.5 3.97E–05 117.57 –15.94 –2.29 585.32 0.000 0.000

7/19 8:53 103 1245 1246 2 0 –0.027 –0.01 26.27 0.00 314.93 540.82 0.0 0.00E+00 314.9 540.8 3.39E–04 0.00 –26.18 0.00 0.00 0.000 0.000

7/19 10:21 104 1247 1255 1 0 B4–A1 –0.03 25.18 0.00 3657.65 611.33 4.6 1.49E+06 11.2 116.8 5.57E–05 165.38 –12.71 16.07 578.69 0.000 0.000

7/19 10:26 105 1256 1264 1 0 B4–A1 59.59 25.19 0.00 3657.58 610.78 4.6 1.50E+06 11.2 116.7 5.57E–05 165.38 –12.71 16.13 579.23 0.000 0.000

7/19 10:31 106 1265 1273 1 0 B4–A1 120.37 25.19 0.00 3657.55 610.74 4.6 1.50E+06 11.2 116.7 5.57E–05 165.37 –12.71 16.19 579.72 0.000 0.000

7/19 10:36 107 1274 1282 1 0 B4–A1 179.93 25.19 0.00 3657.43 610.30 4.6 1.50E+06 11.2 116.6 5.58E–05 165.37 –12.71 16.23 580.18 0.000 0.000

7/19 10:45 108 1283 1291 1 0 B4–A1 179.93 40.15 0.00 3657.60 610.14 4.6 1.50E+06 11.2 116.6 5.58E–05 165.38 –12.71 16.28 581.03 0.000 0.000

7/19 10:50 109 1292 1300 1 0 B4–A1 120.33 40.15 0.00 3657.72 610.24 4.6 1.50E+06 11.2 116.6 5.58E–05 165.38 –12.70 16.29 581.37 0.000 0.000

7/19 10:55 110 1301 1309 1 0 B4–A1 59.53 40.15 0.00 3657.74 610.16 4.6 1.50E+06 11.2 116.6 5.58E–05 165.38 –11.00 16.30 581.64 0.000 0.000

7/19 11:01 111 1310 1318 1 0 B4–A1 –0.01 40.09 0.00 3657.43 609.96 4.6 1.50E+06 11.2 116.6 5.58E–05 165.37 –11.46 16.30 582.06 0.000 0.000

7/19 11:08 112 1319 1327 1 0 B4–A1 –0.01 50.19 0.00 3657.48 610.01 4.6 1.50E+06 11.2 116.6 5.58E–05 165.37 –11.52 16.33 582.45 0.000 0.000

7/19 11:13 113 1328 1336 1 0 B4–A1 59.61 50.19 0.00 3657.77 610.04 4.6 1.50E+06 11.2 116.6 5.58E–05 165.38 –11.58 16.36 582.71 0.000 0.000

7/19 11:18 114 1337 1345 1 0 B4–A1 120.45 50.19 0.00 3657.67 610.01 4.6 1.50E+06 11.2 116.6 5.58E–05 165.38 –11.59 16.40 582.92 0.000 0.000

7/19 11:23 115 1346 1354 1 0 B4–A1 179.97 50.19 0.00 3657.77 609.83 4.6 1.50E+06 11.2 116.6 5.58E–05 165.38 –11.67 16.43 583.16 0.000 0.000

7/19 11:32 116 1355 1363 1 0 B4–A1 179.97 50.19 8.00 3657.65 609.98 4.6 1.50E+06 11.2 116.6 5.58E–05 165.38 –11.67 16.46 583.79 0.000 0.000

7/19 11:37 117 1364 1372 1 0 B4–A1 120.33 50.19 8.00 3657.55 609.80 4.6 1.50E+06 11.2 116.6 5.58E–05 165.37 –11.67 16.46 584.10 0.000 0.000

7/19 11:42 118 1373 1381 1 0 B4–A1 59.55 50.19 8.00 3657.41 609.98 4.6 1.50E+06 11.2 116.6 5.58E–05 165.37 –11.67 16.46 584.43 0.000 0.000

7/19 11:48 119 1382 1390 1 0 B4–A1 0.03 50.19 8.00 3657.89 609.84 4.6 1.50E+06 11.2 116.6 5.58E–05 165.39 –11.58 16.46 584.72 0.000 0.000

7/19 12:00 120 1391 1400 1 0 B4–A1 0.03 25.16 –8.00 3657.66 609.78 4.6 1.50E+06 11.2 116.5 5.58E–05 165.38 –11.49 16.49 585.37 0.000 0.000

7/19 12:05 121 1401 1409 1 0 B4–A1 59.65 25.16 –8.00 3657.62 609.90 4.6 1.50E+06 11.2 116.6 5.58E–05 165.38 –11.38 16.51 585.40 0.000 0.000

7/19 12:09 122 1410 1418 1 0 B4–A1 120.41 25.16 –8.00 3657.74 609.60 4.6 1.50E+06 11.2 116.5 5.58E–05 165.38 –11.35 16.54 585.34 0.000 0.000

7/19 12:14 123 1419 1427 1 0 B4–A1 179.93 25.16 –8.00 3657.65 609.62 4.6 1.50E+06 11.2 116.5 5.58E–05 165.38 –11.28 16.56 585.36 0.000 0.000

7/20 12:22 124 1431 1435 5 0 –0.014 49.73 27.56 0.00 0.00 552.30 0.0 0.00E+00 0.0 552.3 0.00E+00 0.00 65.91 0.00 0.00 0.000 0.000

7/20 13:26 125 1436 1437 2 0 B4–A1 26.64 33.85 0.00 2123.60 550.59 0.0 0.00E+00 2123.6 550.6 2.25E–03 0.00 64.76 0.00 0.00 0.000 0.000

7/20 15:25 129 1509 1946 4 0 B4–A1 –0.01 40.13 0.00 2130.49 547.97 0.0 0.00E+00 2130.5 548.0 2.26E–03 0.00 65.48 889.11 572.34 0.000 0.000

7/21 6:59 131 1947 1947 2 1 –0.054 –0.01 26.77 0.00 2123.92 545.84 0.0 0.00E+00 2123.9 545.8 2.27E–03 0.00 66.48 0.00 0.00 0.000 0.000

7/22 7:09 135 1951 1953 2 1 –0.057 –0.01 26.77 0.00 2123.49 543.50 0.0 0.00E+00 2123.5 543.5 2.28E–03 0.00 66.12 0.00 0.00 0.000 0.000

7/22 7:56 135 1954 1958 2 1 –0.056 –0.01 26.77 0.00 327.11 532.52 0.0 0.00E+00 327.1 532.5 3.58E–04 0.00 –26.19 0.00 0.00 0.000 0.000

Table B-3. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

136

RUN INFORMATION MODEL ATTITUDE & LOCATION RUN-AVERAGED FLOW CONDITIONS NOZZLE EXIT CONDITIONS

DATE TIME RUN POINT

Key # 

NOZ

PITCH ROLL X_STRUT Y_STRUT PTINF TTINF MACH REINF PINF TINF RHOINF QINF DEWPT PTJ TTJ WJ CT

2010 START END {deg} {deg} {in} {in} {psf} {R} {1/ft} {psf} {R} {slug/ft^3} {psf} {deg F} {psia} {R} {lbm/sec}

7/22 9:09 136 1959 1964 1 1 B4–A3 –0.01 40.16 0.00 778.03 594.64 2.4 1.00E+06 53.2 276.3 1.12E–04 214.57 –25.56 1551.23 637.33 1.642 4.024

7/22 9:38 137 1965 1970 1 1 B4–A3 –0.03 40.15 0.00 778.14 594.73 2.4 1.00E+06 53.2 276.4 1.12E–04 214.60 –25.40 1162.84 630.66 1.228 3.002

7/22 9:50 138 1971 1978 1 1 B4–A2 179.97 40.15 0.00 777.92 594.68 2.4 9.99E+05 53.2 276.3 1.12E–04 214.54 –25.36 1165.00 633.93 1.228 3.012

7/22 10:04 139 1979 1988 1 1 B4–A1 179.97 40.15 0.00 777.88 594.55 2.4 1.00E+06 53.2 276.3 1.12E–04 214.53 –25.36 388.43 624.75 0.393 0.968

7/22 10:11 140 1989 1997 1 1 B4–A1 –0.03 40.15 0.00 778.06 594.82 2.4 9.99E+05 53.2 276.4 1.12E–04 214.58 –25.11 387.98 624.28 0.393 0.967

7/22 10:22 141 1998 2006 1 1 B4–A1 –0.03 40.15 0.00 777.72 594.68 2.4 9.99E+05 53.2 276.3 1.12E–04 214.48 –24.96 775.00 638.08 0.801 1.982

7/22 10:27 142 2007 2015 1 1 B4–A1 –179.91 40.15 0.00 777.84 594.56 2.4 1.00E+06 53.2 276.3 1.12E–04 214.52 –25.18 776.77 643.54 0.798 1.983

7/22 10:55 143 2016 2024 1 1 B4–A1 –179.91 40.15 0.00 777.96 594.72 2.4 9.99E+05 53.2 276.4 1.12E–04 214.55 –24.82 194.06 620.04 0.190 0.468

7/22 11:00 144 2025 2033 1 1 B4–A1 0.01 40.15 0.00 777.96 594.61 2.4 1.00E+06 53.2 276.3 1.12E–04 214.55 –24.89 194.07 618.78 0.188 0.464

7/22 11:08 145 2034 2042 1 1 B4–A1 0.01 40.15 0.00 777.89 594.59 2.4 1.00E+06 53.2 276.3 1.12E–04 214.53 –24.89 96.65 606.25 0.093 0.228

7/22 11:14 146 2043 2051 1 1 B4–A1 60.00 40.15 0.00 778.08 594.67 2.4 1.00E+06 53.2 276.3 1.12E–04 214.58 –24.89 96.83 603.33 0.093 0.228

7/22 11:20 147 2052 2055 1 1 B4–A1 89.99 40.15 0.00 778.09 594.80 2.4 9.99E+05 53.2 276.4 1.12E–04 214.59 –24.89 86.21 600.43 0.083 0.201

7/22 11:31 148 2056 2064 1 1 B4–A1 60.00 40.15 0.00 777.74 594.65 2.4 9.99E+05 53.2 276.3 1.12E–04 214.49 –25.42 3.87 592.00 0.000 0.000

7/22 11:37 149 2065 2073 1 1 B4–A1 –0.03 40.15 0.00 778.58 594.95 2.4 1.00E+06 53.3 276.5 1.12E–04 214.72 –22.18 3.78 590.26 0.000 0.000

7/22 12:23 150 2074 2082 1 1 B4–A1 –0.03 40.17 0.00 1386.07 594.48 3.5 1.00E+06 18.2 172.3 6.14E–05 155.83 –21.75 848.84 639.79 0.873 2.978

7/22 12:29 151 2083 2091 1 1 B4–A1 –179.97 40.17 0.00 1386.19 594.84 3.5 9.99E+05 18.2 172.4 6.14E–05 155.84 –21.16 850.00 637.95 0.874 2.977

7/22 12:37 152 2092 2100 1 1 B4–A1 –179.97 40.17 0.00 1386.43 594.71 3.5 9.99E+05 18.2 172.4 6.14E–05 155.87 –21.19 562.87 630.63 0.577 1.960

7/22 12:42 153 2101 2109 1 1 B4–A1 –0.09 40.17 0.00 1386.58 594.86 3.5 9.99E+05 18.2 172.4 6.14E–05 155.89 –21.19 563.40 628.33 0.579 1.962

7/22 12:51 154 2110 2118 1 1 B4–A1 –0.09 40.17 0.00 1387.10 594.57 3.5 1.00E+06 18.2 172.3 6.15E–05 155.95 –20.20 281.32 621.69 0.276 0.938

7/22 13:21 155 2119 2127 1 1 B4–A1 179.92 40.17 0.00 1386.24 593.98 3.5 1.00E+06 18.2 172.2 6.15E–05 155.85 –21.94 282.60 617.63 0.281 0.950

7/22 13:31 156 2128 2136 1 1 B4–A1 179.93 40.17 0.00 1386.31 594.66 3.5 9.99E+05 18.2 172.4 6.14E–05 155.86 –21.72 139.65 609.19 0.134 0.452

7/22 13:36 157 2137 2145 1 1 B4–A1 0.07 40.17 0.00 1386.43 594.64 3.5 1.00E+06 18.2 172.4 6.14E–05 155.87 –21.62 140.12 607.70 0.133 0.448

7/22 13:45 158 2146 2154 5 1 B4–A1 0.07 40.17 0.00 1386.91 594.52 3.5 1.00E+06 18.2 172.3 6.14E–05 155.92 –18.42 70.02 597.83 0.063 0.210

7/22 14:32 159 2155 2163 1 1 B4–A1 0.00 40.17 0.00 1386.70 594.65 3.5 1.00E+06 18.2 172.4 6.14E–05 155.90 –21.22 69.88 605.89 0.062 0.210

7/22 14:37 160 2164 2172 1 1 B4–A1 179.93 40.17 0.00 1386.48 594.56 3.5 1.00E+06 18.2 172.3 6.14E–05 155.88 –21.15 69.75 601.42 0.062 0.210

7/22 14:43 161 2173 2181 1 1 B4–A1 179.93 40.17 0.00 1386.38 594.69 3.5 9.99E+05 18.2 172.4 6.14E–05 155.87 –21.06 3.29 594.81 0.000 0.000

7/22 14:49 162 2182 2190 1 1 B4–A1 0.03 40.17 0.00 1386.41 594.90 3.5 9.99E+05 18.2 172.4 6.14E–05 155.87 –20.96 3.08 591.54 0.000 0.000

7/22 15:53 163 2191 2199 1 1 B4–A1 0.03 40.17 0.00 3658.90 610.12 4.6 1.50E+06 11.2 116.6 5.58E–05 165.43 –6.33 896.53 634.14 0.926 2.959

7/22 16:00 164 2200 2208 1 1 B4–A1 179.93 40.17 0.00 3658.18 609.73 4.6 1.50E+06 11.2 116.5 5.58E–05 165.40 –9.80 900.08 628.66 0.931 2.960

7/22 16:11 165 2209 2217 1 1 B4–A1 179.93 40.15 0.00 3657.58 609.60 4.6 1.50E+06 11.2 116.5 5.58E–05 165.38 –10.81 598.93 622.08 0.620 1.968

7/22 16:17 166 2218 2226 1 1 B4–A1 0.03 40.15 0.00 3657.24 609.85 4.6 1.50E+06 11.2 116.6 5.58E–05 165.36 –10.81 598.09 621.86 0.619 1.966

7/22 16:25 167 2227 2235 1 1 B4–A1 0.03 40.15 0.00 3657.89 609.69 4.6 1.50E+06 11.2 116.5 5.58E–05 165.39 –10.81 298.58 617.13 0.296 0.943

Table B-3. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

137

RUN INFORMATION MODEL ATTITUDE & LOCATION RUN-AVERAGED FLOW CONDITIONS NOZZLE EXIT CONDITIONS

DATE TIME RUN POINT

Key # 

NOZ

PITCH ROLL X_STRUT Y_STRUT PTINF TTINF MACH REINF PINF TINF RHOINF QINF DEWPT PTJ TTJ WJ CT

2010 START END {deg} {deg} {in} {in} {psf} {R} {1/ft} {psf} {R} {slug/ft^3} {psf} {deg F} {psia} {R} {lbm/sec}

7/22 16:31 168 2236 2244 1 1 B4–A1 179.95 40.15 0.00 3657.53 609.60 4.6 1.50E+06 11.2 116.5 5.58E–05 165.37 –10.80 298.20 618.12 0.294 0.938

7/22 16:39 169 2245 2253 1 1 B4–A1 179.95 40.15 0.00 3657.58 609.82 4.6 1.50E+06 11.2 116.6 5.58E–05 165.38 –8.49 148.09 613.28 0.142 0.454

7/22 16:44 170 2254 2262 1 1 B4–A1 0.03 40.15 0.00 3658.18 609.52 4.6 1.50E+06 11.2 116.5 5.58E–05 165.40 –8.85 148.23 612.11 0.143 0.455

7/22 16:52 171 2263 2271 1 1 B4–A1 0.03 40.15 0.00 3657.91 609.60 4.6 1.50E+06 11.2 116.5 5.58E–05 165.39 –9.74 74.45 604.78 0.069 0.219

7/22 16:57 172 2272 2280 1 1 B4–A1 179.92 40.15 0.00 3657.55 609.74 4.6 1.50E+06 11.2 116.5 5.58E–05 165.37 –10.72 74.51 601.98 0.069 0.219

7/22 17:02 173 2281 2289 1 1 B4–A1 179.91 40.15 0.00 3657.14 609.86 4.6 1.50E+06 11.2 116.6 5.58E–05 165.36 –10.72 3.36 597.47 0.000 0.000

7/22 17:07 174 2290 2298 1 1 B4–A1 –0.07 40.15 0.00 3657.58 609.93 4.6 1.50E+06 11.2 116.6 5.58E–05 165.38 –10.72 3.20 594.66 0.000 0.000

7/22 17:16 175 2299 2300 3 1 0.022 –0.07 40.15 0.00 893.38 588.35 0.0 0.00E+00 893.4 588.4 8.85E–04 0.00 –19.25 0.00 0.00 0.000 0.000

7/22 17:18 175 2301 2301 3 1 –0.1 –0.07 40.15 0.00 2117.23 614.95 0.0 0.00E+00 2117.2 615.0 2.01E–03 0.00 –21.22 0.00 0.00 0.000 0.000

7/23 14:20 178 2305 2305 2 3 0.356 0.09 40.15 0.00 320.54 548.53 0.0 0.00E+00 320.5 548.5 3.40E–04 0.00 2.51 0.00 0.00 0.000 0.000

7/23 15:05 179 2307 2543 1 3 0.349 0.09 40.15 0.00 778.07 595.28 2.4 9.98E+05 53.2 276.6 1.12E–04 214.58 –23.91 vary 560.06 vary vary

7/23 15:41 180 2544 2554 1 3 B4–A1 0.00 40.15 0.00 777.80 594.54 2.4 1.00E+06 53.2 276.3 1.12E–04 214.51 –28.15 3.93 588.07 0.000 0.000

7/23 15:49 181 2555 2563 1 3 B4–A1 179.97 40.15 0.00 778.32 594.47 2.4 1.00E+06 53.2 276.2 1.12E–04 214.65 –28.13 3.85 586.35 0.000 0.000

7/23 15:54 182 2564 2572 1 3 B4–A1 120.37 40.15 0.00 778.27 594.75 2.4 1.00E+06 53.2 276.4 1.12E–04 214.64 –27.80 3.85 585.87 0.000 0.000

7/23 15:59 183 2573 2581 1 3 B4–A1 59.63 40.15 0.00 777.96 594.74 2.4 9.99E+05 53.2 276.4 1.12E–04 214.55 –27.52 3.78 585.34 0.000 0.000

7/23 16:21 184 2582 2590 1 3 B4–A1 0.05 40.15 0.00 1387.15 593.53 3.5 1.00E+06 18.2 172.0 6.16E–05 155.95 –21.66 2.96 583.95 0.000 0.000

7/23 16:27 185 2591 2599 1 3 B4–A1 59.53 40.15 0.00 1387.13 594.97 3.5 9.99E+05 18.2 172.5 6.14E–05 155.95 –21.43 2.90 583.39 0.000 0.000

7/23 16:32 186 2600 2608 1 3 B4–A1 120.35 40.15 0.00 1387.08 594.58 3.5 1.00E+06 18.2 172.3 6.15E–05 155.94 –21.34 2.93 582.99 0.000 0.000

7/23 16:37 187 2609 2617 1 3 B4–A1 179.96 40.15 0.00 1386.84 594.75 3.5 1.00E+06 18.2 172.4 6.14E–05 155.92 –21.34 2.89 582.52 0.000 0.000

7/23 16:45 188 2618 2619 3 3 –0.056 –0.01 40.15 0.00 196.45 583.65 0.0 0.00E+00 196.4 583.6 1.96E–04 0.00 –21.34 0.00 0.00 0.000 0.000

7/23 16:49 188 2620 2620 3 3 –0.1 –0.01 40.15 0.00 2117.88 616.76 0.0 0.00E+00 2117.9 616.8 2.00E–03 0.00 –21.34 0.00 0.00 0.000 0.000

7/26 7:55 189 2621 2622 2 3 –0.124 –2.72 40.15 0.00 2125.43 546.27 0.0 0.00E+00 2125.4 546.3 2.27E–03 0.00 64.70 0.00 0.00 0.000 0.000

7/26 8:25 189 2623 2624 2 3 –0.124 –2.72 40.15 0.00 380.37 522.52 0.0 0.00E+00 380.4 522.5 4.24E–04 0.00 –22.60 0.00 0.00 0.000 0.000

7/26 9:26 190 2625 2633 1 3 B4–A1 –0.01 40.15 0.00 777.98 594.57 2.4 1.00E+06 53.2 276.3 1.12E–04 214.56 –27.60 391.69 633.39 1.186 2.939

7/26 9:31 191 2634 2641 1 3 B4–A1 59.48 40.15 0.00 777.82 594.57 2.4 1.00E+06 53.2 276.3 1.12E–04 214.51 –27.30 389.25 637.75 1.177 2.926

7/26 9:47 192 2642 2649 1 3 B4–A2 120.21 40.15 0.00 777.95 595.29 2.4 9.98E+05 53.2 276.6 1.12E–04 214.55 –23.28 391.13 635.92 1.185 2.943

7/26 10:09 193 2650 2657 1 3 B4–A2 –179.97 40.15 0.00 777.90 594.68 2.4 9.99E+05 53.2 276.3 1.12E–04 214.53 –26.04 392.77 638.96 1.185 2.950

7/26 10:24 194 2658 2666 1 3 B4–A1 –179.97 40.15 0.00 778.20 594.64 2.4 1.00E+06 53.2 276.3 1.12E–04 214.62 –26.04 260.46 623.73 0.788 1.940

7/26 10:29 195 2667 2675 1 3 B4–A1 120.37 40.15 0.00 777.86 594.57 2.4 1.00E+06 53.2 276.3 1.12E–04 214.52 –26.05 259.56 618.32 0.789 1.935

7/26 10:34 196 2676 2684 1 3 B4–A1 59.53 40.15 0.00 777.94 594.62 2.4 1.00E+06 53.2 276.3 1.12E–04 214.54 –26.05 258.82 617.07 0.787 1.929

7/26 10:39 197 2685 2693 1 3 B4–A1 –0.01 40.15 0.00 777.91 594.76 2.4 9.99E+05 53.2 276.4 1.12E–04 214.54 –26.25 259.10 617.30 0.788 1.931

7/26 10:48 198 2694 2702 1 3 B4–A1 –0.01 40.15 0.00 777.91 594.51 2.4 1.00E+06 53.2 276.3 1.12E–04 214.54 –24.46 130.51 615.45 0.384 0.944

Table B-3. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

138

RUN INFORMATION MODEL ATTITUDE & LOCATION RUN-AVERAGED FLOW CONDITIONS NOZZLE EXIT CONDITIONS

DATE TIME RUN POINT

Key # 

NOZ

PITCH ROLL X_STRUT Y_STRUT PTINF TTINF MACH REINF PINF TINF RHOINF QINF DEWPT PTJ TTJ WJ CT

2010 START END {deg} {deg} {in} {in} {psf} {R} {1/ft} {psf} {R} {slug/ft^3} {psf} {deg F} {psia} {R} {lbm/sec}

7/26 10:53 199 2703 2711 1 3 B4–A1 59.57 40.15 0.00 778.10 594.79 2.4 9.99E+05 53.2 276.4 1.12E–04 214.59 –21.69 130.11 616.73 0.382 0.939

7/26 10:58 200 2712 2720 1 3 B4–A1 120.35 40.15 0.00 778.06 594.66 2.4 1.00E+06 53.2 276.3 1.12E–04 214.58 –21.83 130.32 616.57 0.382 0.941

7/26 11:03 201 2721 2729 1 3 B4–A1 179.99 40.15 0.00 777.96 594.54 2.4 1.00E+06 53.2 276.3 1.12E–04 214.55 –22.17 130.87 617.04 0.384 0.946

7/26 11:17 202 2730 2738 1 3 B4–A1 179.99 40.15 0.00 777.89 594.58 2.4 1.00E+06 53.2 276.3 1.12E–04 214.53 –22.74 63.93 607.59 0.175 0.431

7/26 11:38 203 2739 2747 1 3 B4–A1 –179.97 40.15 0.00 778.01 594.64 2.4 1.00E+06 53.2 276.3 1.12E–04 214.56 –23.03 64.16 607.24 0.178 0.437

7/26 11:43 204 2748 2756 1 3 B4–A1 120.39 40.15 0.00 777.94 594.83 2.4 9.99E+05 53.2 276.4 1.12E–04 214.54 –23.03 63.88 606.28 0.177 0.436

7/26 11:48 205 2757 2765 1 3 B4–A1 59.53 40.15 0.00 778.13 594.80 2.4 9.99E+05 53.2 276.4 1.12E–04 214.60 –22.99 63.97 606.76 0.176 0.433

7/26 11:54 206 2766 2774 1 3 B4–A1 –0.05 40.15 0.00 778.01 594.44 2.4 1.00E+06 53.2 276.2 1.12E–04 214.56 –22.94 63.71 606.00 0.177 0.435

7/26 12:07 207 2775 2775 3 3 –0.121 –0.01 40.15 0.00 2126.51 614.20 0.0 0.00E+00 2126.5 614.2 2.97E–04 0.00 –0.61 0.00 0.00 0.000 0.000

7/26 12:48 208 2776 2776 2 3 –0.125 9.33 40.15 0.00 2127.60 579.24 0.0 0.00E+00 2127.6 579.2 2.14E–03 0.00 35.04 0.00 0.00 0.000 0.000

7/26 13:09 208 2777 2778 2 3 –0.124 9.33 40.15 0.00 331.34 564.63 0.0 0.00E+00 331.3 564.6 3.42E–04 0.00 –21.87 0.00 0.00 0.000 0.000

7/26 14:37 210 2780 2785 5 3 –0.137 –0.29 40.15 0.00 2143.08 584.51 0.0 4.12E+06 2143.1 584.5 2.14E–03 0.00 70.32 vary 601.83 vary vary

7/26 16:40 211 2786 2793 1 3 B4–A2 –0.03 40.15 0.00 3658.04 609.79 4.6 1.50E+06 11.2 116.6 5.58E–05 165.40 –6.84 303.50 625.48 0.916 2.932

7/26 16:45 212 2794 2801 1 3 B4–A2 59.76 40.15 0.00 3657.91 609.84 4.6 1.50E+06 11.2 116.6 5.58E–05 165.39 –6.73 303.28 627.67 0.915 2.933

7/26 16:49 213 2802 2809 1 3 B4–A2 120.25 40.15 0.00 3657.85 609.73 4.6 1.50E+06 11.2 116.5 5.58E–05 165.39 –6.67 302.03 626.89 0.911 2.919

7/26 16:55 214 2810 2817 1 3 B4–A2 179.99 40.15 0.00 3657.93 609.76 4.6 1.50E+06 11.2 116.5 5.58E–05 165.39 –6.59 305.05 625.47 0.924 2.954

7/26 17:06 215 2818 2819 3 3 –0.126 –0.01 40.15 0.00 382.32 566.49 0.0 0.00E+00 382.3 566.5 3.93E–04 0.00 –6.63 0.00 0.00 0.000 0.000

7/26 17:12 215 2820 2820 3 3 –0.122 –0.01 40.15 0.00 2124.14 609.57 0.0 0.00E+00 2124.1 609.6 2.03E–03 0.00 –2.08 0.00 0.00 0.000 0.000

7/27 7:55 216 2821 2821 2 3 –0.115 –0.03 40.15 0.00 2131.05 562.34 0.0 0.00E+00 2131.1 562.3 2.21E–03 0.00 53.02 0.00 0.00 0.000 0.000

7/27 8:24 216 2822 2823 2 3 –0.109 –0.03 40.15 0.00 318.71 553.19 0.0 0.00E+00 318.7 553.2 3.36E–04 0.00 –20.13 0.00 0.00 0.000 0.000

7/27 9:18 217 2824 2832 1 3 B4–A1 –0.03 40.15 0.00 777.82 594.80 2.4 9.99E+05 53.2 276.4 1.12E–04 214.51 –26.81 69.29 608.03 0.193 0.474

7/27 9:23 218 2833 2841 1 3 B4–A1 59.53 40.15 0.00 777.91 594.77 2.4 9.99E+05 53.2 276.4 1.12E–04 214.54 –27.16 69.60 610.18 0.194 0.478

7/27 9:28 219 2842 2850 1 3 B4–A1 120.37 40.15 0.00 777.82 594.55 2.4 1.00E+06 53.2 276.3 1.12E–04 214.51 –27.28 69.58 609.56 0.193 0.476

7/27 9:33 220 2851 2859 1 3 B4–A1 179.95 40.15 0.00 777.77 594.65 2.4 9.99E+05 53.2 276.3 1.12E–04 214.50 –27.17 69.98 610.07 0.195 0.479

7/27 9:40 221 2860 2868 1 3 B4–A1 –0.01 40.15 0.00 777.48 594.68 2.4 9.99E+05 53.2 276.3 1.12E–04 214.42 –27.17 36.40 601.17 0.096 0.235

7/27 11:17 222 2869 2877 1 3 B4–A1 –0.01 40.15 0.00 1386.60 594.59 3.5 1.00E+06 18.2 172.3 6.14E–05 155.89 –16.75 288.71 623.35 0.874 2.963

7/27 11:22 223 2878 2886 1 3 B4–A1 59.55 40.15 0.00 1385.98 594.25 3.5 1.00E+06 18.2 172.2 6.15E–05 155.82 –16.53 289.79 623.22 0.876 2.971

7/27 11:26 224 2887 2895 1 3 B4–A1 120.41 40.15 0.00 1386.86 595.00 3.5 9.99E+05 18.2 172.5 6.14E–05 155.92 –16.09 288.61 622.75 0.876 2.966

7/27 11:34 225 2896 2904 1 3 B4–A1 179.97 40.15 0.00 1386.86 594.99 3.5 9.99E+05 18.2 172.5 6.14E–05 155.92 –15.84 290.89 622.12 0.882 2.985

7/27 11:56 226 2905 2913 1 3 B4–A1 179.97 40.15 0.00 1386.19 594.77 3.5 9.99E+05 18.2 172.4 6.14E–05 155.84 –14.89 192.86 619.18 0.578 1.956

7/27 12:05 227 2914 2922 1 3 B4–A1 120.39 40.15 0.00 1386.10 595.12 3.5 9.98E+05 18.2 172.5 6.14E–05 155.83 –15.03 192.14 619.05 0.575 1.948

7/27 12:10 228 2923 2934 1 3 B4–A1 59.61 40.15 0.00 1385.81 593.98 3.5 1.00E+06 18.2 172.2 6.15E–05 155.80 –14.72 191.76 619.68 0.574 1.944

Table B-3. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

139

RUN INFORMATION MODEL ATTITUDE & LOCATION RUN-AVERAGED FLOW CONDITIONS NOZZLE EXIT CONDITIONS

DATE TIME RUN POINT

Key # 

NOZ

PITCH ROLL X_STRUT Y_STRUT PTINF TTINF MACH REINF PINF TINF RHOINF QINF DEWPT PTJ TTJ WJ CT

2010 START END {deg} {deg} {in} {in} {psf} {R} {1/ft} {psf} {R} {slug/ft^3} {psf} {deg F} {psia} {R} {lbm/sec}

7/27 12:15 229 2935 2940 1 3 B4–A1 –0.02 40.15 0.00 1386.94 595.07 3.5 9.99E+05 18.2 172.5 6.14E–05 155.93 –14.75 191.94 619.60 0.575 1.947

7/27 12:28 230 2941 2949 1 3 B4–A1 –0.03 40.15 0.00 1387.32 594.47 3.5 1.00E+06 18.2 172.3 6.15E–05 155.97 –14.46 98.99 614.50 0.284 0.962

7/27 12:54 231 2950 2951 3 3 –0.122 –0.01 40.15 0.00 188.46 583.73 0.0 0.00E+00 188.5 583.7 1.88E–04 0.00 –16.38 0.00 0.00 0.000 0.000

7/27 13:07 231 2952 2952 3 3 –0.118 –0.01 40.15 0.00 2130.62 589.58 0.0 0.00E+00 2130.6 589.6 2.11E–03 0.00 5.68 0.00 0.00 0.000 0.000

7/27 14:43 232 2953 2954 2 3 –0.119 –0.01 40.15 0.00 340.52 566.09 0.0 0.00E+00 340.5 566.1 3.50E–04 0.00 –35.22 0.00 0.00 0.000 0.000

7/27 15:12 233 2955 2963 1 3 B4–A1 59.55 40.15 0.00 1386.79 594.65 3.5 1.00E+06 18.2 172.4 6.15E–05 155.91 –24.56 98.39 590.80 0.290 0.964

7/27 15:17 234 2964 2972 1 3 B4–A1 –0.05 40.15 0.00 1386.79 594.77 3.5 1.00E+06 18.2 172.4 6.14E–05 155.91 –24.32 98.58 593.97 0.291 0.968

7/27 15:22 235 2973 2981 1 3 B4–A1 120.41 40.15 0.00 1386.74 594.62 3.5 1.00E+06 18.2 172.4 6.15E–05 155.91 –24.06 98.45 596.85 0.288 0.960

7/27 15:27 236 2982 2990 1 3 B4–A1 179.95 40.15 0.00 1386.29 594.70 3.5 9.99E+05 18.2 172.4 6.14E–05 155.86 –23.96 99.16 599.79 0.289 0.967

7/27 15:41 237 2991 3001 1 3 B4–A1 179.95 40.15 0.00 1387.58 594.01 3.5 1.00E+06 18.2 172.2 6.16E–05 156.00 –21.66 50.14 597.64 0.137 0.461

7/27 15:47 238 3002 3010 1 3 B4–A1 120.35 40.15 0.00 1387.22 595.20 3.5 9.99E+05 18.2 172.5 6.14E–05 155.96 –18.03 50.64 597.72 0.138 0.465

7/27 15:55 239 3011 3019 1 3 B4–A1 59.59 40.15 0.00 1387.44 595.14 3.5 9.99E+05 18.2 172.5 6.14E–05 155.98 –15.92 50.70 598.96 0.137 0.463

7/27 16:01 240 3020 3028 1 3 B4–A1 –0.05 40.15 0.00 1386.50 594.27 3.5 1.00E+06 18.2 172.3 6.15E–05 155.88 –16.22 50.76 599.95 0.137 0.462

7/27 16:12 241 3029 3037 1 3 B4–A1 –0.05 40.15 0.00 1386.50 594.27 3.5 1.00E+06 18.2 172.3 6.15E–05 155.88 –18.72 26.62 593.41 0.067 0.225

7/27 16:42 242 3038 3046 1 3 B4–A1 –0.05 40.15 0.00 3657.74 609.76 4.6 1.50E+06 11.2 116.5 5.58E–05 165.38 –0.62 205.41 624.32 0.611 1.959

7/27 16:47 243 3047 3055 1 3 B4–A1 59.59 40.15 0.00 3657.96 609.60 4.6 1.50E+06 11.2 116.5 5.58E–05 165.39 –2.36 205.03 626.00 0.609 1.955

7/27 16:52 244 3056 3064 1 3 B4–A1 120.41 40.15 0.00 3657.86 609.79 4.6 1.50E+06 11.2 116.5 5.58E–05 165.39 –3.55 205.47 625.65 0.612 1.962

7/27 16:57 245 3065 3073 1 3 B4–A1 –179.99 40.15 0.00 3658.13 609.73 4.6 1.50E+06 11.2 116.5 5.58E–05 165.40 –3.69 206.20 624.94 0.615 1.970

7/27 17:05 246 3074 3075 3 3 –0.147 –0.03 40.15 0.00 388.15 571.36 0.0 0.00E+00 388.2 571.4 3.96E–04 0.00 –24.54 0.00 0.00 0.000 0.000

7/27 17:09 246 3076 3076 3 3 –0.144 –0.03 40.15 0.00 2127.16 619.12 0.0 0.00E+00 2127.2 619.1 2.00E–03 0.00 –27.46 0.00 0.00 0.000 0.000

7/28 8:36 247 3080 3089 1 3 B4–A1 –0.03 40.15 0.00 3658.01 610.37 4.6 1.50E+06 11.2 116.7 5.58E–05 165.39 –11.11 201.19 623.56 0.599 1.919

7/28 8:42 248 3090 3098 1 3 B4–A1 179.99 40.15 0.00 3657.94 610.45 4.6 1.50E+06 11.2 116.7 5.58E–05 165.39 –11.71 202.53 629.30 0.600 1.930

7/28 8:51 249 3099 3107 1 3 B4–A1 179.99 40.15 0.00 3657.94 610.08 4.6 1.50E+06 11.2 116.6 5.58E–05 165.39 –12.24 99.14 627.41 0.278 0.898

7/28 8:56 250 3108 3116 1 3 B4–A1 120.39 40.15 0.00 3657.60 610.25 4.6 1.50E+06 11.2 116.6 5.58E–05 165.38 –12.59 99.11 628.12 0.279 0.901

7/28 9:01 251 3117 3125 1 3 B4–A1 59.63 40.15 0.00 3658.51 610.21 4.6 1.50E+06 11.2 116.6 5.58E–05 165.42 –12.69 98.99 628.82 0.277 0.897

7/28 9:06 252 3126 3134 1 3 B4–A1 –0.03 40.15 0.00 3657.79 610.16 4.6 1.50E+06 11.2 116.6 5.58E–05 165.38 –12.81 99.16 628.48 0.277 0.898

7/28 9:16 253 3135 3143 1 3 B4–A1 –0.03 40.15 0.00 3657.98 609.88 4.6 1.50E+06 11.2 116.6 5.58E–05 165.39 –12.96 49.92 618.75 0.132 0.428

7/28 9:21 254 3144 3152 1 3 B4–A1 59.59 40.15 0.00 3657.96 609.94 4.6 1.50E+06 11.2 116.6 5.58E–05 165.39 –12.86 49.59 617.58 0.132 0.425

7/28 9:26 255 3153 3161 1 3 B4–A1 120.37 40.15 0.00 3657.86 609.99 4.6 1.50E+06 11.2 116.6 5.58E–05 165.39 –12.84 49.55 616.14 0.130 0.421

7/28 9:31 256 3162 3170 1 3 B4–A1 179.95 40.15 0.00 3657.96 609.90 4.6 1.50E+06 11.2 116.6 5.58E–05 165.39 –12.75 49.75 614.95 0.132 0.425

7/28 9:41 257 3171 3179 1 3 B4–A1 –0.03 40.15 0.00 3657.89 609.87 4.6 1.50E+06 11.2 116.6 5.58E–05 165.39 –12.65 25.29 604.69 0.062 0.199

7/28 9:49 258 3180 3188 1 3 B4–A1 –0.03 40.15 0.00 3658.37 609.63 4.6 1.50E+06 11.2 116.5 5.58E–05 165.41 –12.45 3.92 596.86 0.000 0.000

Table B-3. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

140

RUN INFORMATION MODEL ATTITUDE & LOCATION RUN-AVERAGED FLOW CONDITIONS NOZZLE EXIT CONDITIONS

DATE TIME RUN POINT

Key # 

NOZ

PITCH ROLL X_STRUT Y_STRUT PTINF TTINF MACH REINF PINF TINF RHOINF QINF DEWPT PTJ TTJ WJ CT

2010 START END {deg} {deg} {in} {in} {psf} {R} {1/ft} {psf} {R} {slug/ft^3} {psf} {deg F} {psia} {R} {lbm/sec}

7/28 9:55 259 3189 3197 1 3 B4–A1 59.55 40.15 0.00 3658.01 609.76 4.6 1.50E+06 11.2 116.5 5.58E–05 165.39 –12.27 3.75 594.76 0.000 0.000

7/28 10:05 260 3198 3215 1 3 B4–A1 120.35 40.15 0.00 3658.08 609.84 4.6 1.50E+06 11.2 116.6 5.58E–05 165.40 –11.73 3.72 593.30 0.000 0.000

7/28 10:10 261 3216 3224 1 3 B4–A1 179.95 40.15 0.00 3657.96 609.81 4.6 1.50E+06 11.2 116.6 5.58E–05 165.39 –10.97 3.65 592.50 0.000 0.000

7/28 10:23 262 3225 3233 1 3 B4–A2 0.01 40.15 0.00 3656.93 609.76 4.6 1.50E+06 11.2 116.5 5.58E–05 165.35 –10.73 302.81 624.18 0.919 2.937

7/28 10:30 263 3234 3241 1 3 B4–A2 –179.97 40.15 0.00 3657.85 609.99 4.6 1.50E+06 11.2 116.6 5.58E–05 165.39 –10.40 303.07 630.93 0.913 2.935

7/28 11:05 264 3242 3244 1 3 0.015 –60.00 40.16 0.00 3657.82 609.61 4.6 1.50E+06 11.2 116.5 5.58E–05 165.39 –9.37 vary 621.68 vary vary

7/28 11:51 265 3245 3253 1 3 B4–A1 –0.05 40.15 0.00 1387.49 595.15 3.5 9.99E+05 18.2 172.5 6.14E–05 155.99 –25.33 93.69 604.90 0.271 0.912

7/28 12:10 266 3254 3262 1 3 B4–A1 –0.05 40.15 0.00 1386.46 594.96 3.5 9.99E+05 18.2 172.5 6.14E–05 155.87 –24.55 84.78 599.70 0.248 0.830

7/28 12:17 267 3263 3264 1 3 0.031 –0.05 40.15 0.00 1387.26 594.89 3.5 1.00E+06 18.2 172.4 6.14E–05 155.96 –20.23 vary 615.55 vary vary

7/28 12:33 268 3265 3266 3 3 –0.141 –0.01 43.10 0.00 193.86 584.81 0.0 0.00E+00 193.9 584.8 1.93E–04 0.00 –16.55 0.00 0.00 0.000 0.000

7/28 12:36 268 3267 3267 3 3 –0.144 –0.01 43.10 0.00 2123.06 623.54 0.0 0.00E+00 2123.1 623.5 1.98E–03 0.00 –23.93 0.00 0.00 0.000 0.000

7/29 7:27 269 3268 3268 5 0 2.127 –2.76 43.10 0.00 0.00 558.53 0.0 0.00E+00 0.0 558.5 0.00E+00 0.00 59.85 0.00 0.00 0.000 0.000

7/29 15:48 269 3269 3272 2 0 0.278 –0.71 41.09 0.00 2112.53 553.82 0.0 0.00E+00 2112.5 553.8 2.22E–03 0.00 56.42 0.00 0.00 0.000 0.000

7/30 6:42 270 3273 3273 2 0 –0.107 –0.03 40.16 0.00 2113.12 548.57 0.0 0.00E+00 2113.1 548.6 2.24E–03 0.00 64.84 0.00 0.00 0.000 0.000

7/30 7:49 270 3274 3275 2 0 –0.114 –0.03 40.16 0.00 338.47 538.96 0.0 0.00E+00 338.5 539.0 3.66E–04 0.00 9.38 0.00 0.00 0.000 0.000

7/30 8:32 271 3276 3284 1 0 B4–A1 –0.03 40.16 0.00 778.01 594.74 2.4 9.99E+05 53.2 276.4 1.12E–04 214.56 –26.43 1.14 571.08 0.000 0.000

7/30 8:37 272 3285 3293 1 0 B4–A1 59.57 40.16 0.00 777.94 594.64 2.4 1.00E+06 53.2 276.3 1.12E–04 214.54 –26.14 1.19 572.52 0.000 0.000

7/30 8:42 273 3294 3302 1 0 B4–A1 120.35 40.16 0.00 777.98 594.53 2.4 1.00E+06 53.2 276.3 1.12E–04 214.56 –25.53 1.26 573.63 0.000 0.000

7/30 8:49 274 3303 3311 1 0 B4–A1 179.99 40.16 0.00 777.89 594.60 2.4 1.00E+06 53.2 276.3 1.12E–04 214.53 –25.70 1.32 574.73 0.000 0.000

7/30 9:28 276 3312 3321 1 0 B4–A1 179.99 40.16 0.00 1386.83 594.75 3.5 1.00E+06 18.2 172.4 6.14E–05 155.92 –19.86 1.32 576.02 0.000 0.000

7/30 9:33 277 3322 3330 1 0 B4–A1 120.35 40.16 0.00 1386.29 594.92 3.5 9.99E+05 18.2 172.4 6.14E–05 155.86 –20.54 1.28 575.80 0.000 0.000

7/30 9:38 278 3331 3339 1 0 B4–A1 59.61 40.16 0.00 1386.98 594.66 3.5 1.00E+06 18.2 172.4 6.15E–05 155.93 –20.37 1.25 575.91 0.000 0.000

7/30 9:43 279 3340 3348 1 0 B4–A1 –0.05 40.16 0.00 1386.58 594.79 3.5 9.99E+05 18.2 172.4 6.14E–05 155.89 –19.91 1.21 575.90 0.000 0.000

7/30 10:30 280 3349 3357 1 0 B4–A1 –0.05 40.16 0.00 3658.22 609.96 4.6 1.50E+06 11.2 116.6 5.58E–05 165.40 –7.76 1.36 577.72 0.000 0.000

7/30 10:35 281 3358 3366 1 0 B4–A1 59.57 40.16 0.00 3657.91 609.87 4.6 1.50E+06 11.2 116.6 5.58E–05 165.39 –9.96 1.38 578.58 0.000 0.000

7/30 10:40 282 3367 3375 1 0 B4–A1 120.37 40.16 0.00 3658.06 609.90 4.6 1.50E+06 11.2 116.6 5.58E–05 165.40 –10.36 1.39 579.29 0.000 0.000

7/30 10:46 283 3376 3384 1 0 B4–A1 179.96 40.16 0.00 3658.06 609.97 4.6 1.50E+06 11.2 116.6 5.58E–05 165.40 –10.98 1.42 580.20 0.000 0.000

7/30 10:55 283 3385 3386 3 0 –0.137 –0.03 40.16 0.00 373.46 570.50 0.0 0.00E+00 373.5 570.5 3.81E–04 0.00 –24.48 0.00 0.00 0.000 0.000

7/30 10:58 284 3387 3387 3 0 –0.137 –0.03 40.16 0.00 2116.79 614.35 0.0 0.00E+00 2116.8 614.4 2.01E–03 0.00 –29.02 0.00 0.00 0.000 0.000

7/30 14:42 285 3389 3389 5 4 –0.136 –2.76 40.16 0.00 2116.79 570.20 0.0 0.00E+00 2116.8 570.2 2.16E–03 0.00 46.40 0.00 0.00 0.000 0.000

7/30 15:14 285 3390 3391 5 4 –0.128 –2.78 40.16 0.00 357.37 551.56 0.0 0.00E+00 357.4 551.6 3.77E–04 0.00 69.94 0.00 0.00 0.000 0.000

7/30 17:02 286 3392 3392 4 4 –0.002 –0.05 29.69 0.00 1329.26 594.77 0.0 0.00E+00 1329.3 594.8 1.30E–03 0.00 –25.62 271.15 628.94 1.223 2.111

Table B-3. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

141

RUN INFORMATION MODEL ATTITUDE & LOCATION RUN-AVERAGED FLOW CONDITIONS NOZZLE EXIT CONDITIONS

DATE TIME RUN POINT

Key # 

NOZ

PITCH ROLL X_STRUT Y_STRUT PTINF TTINF MACH REINF PINF TINF RHOINF QINF DEWPT PTJ TTJ WJ CT

2010 START END {deg} {deg} {in} {in} {psf} {R} {1/ft} {psf} {R} {slug/ft^3} {psf} {deg F} {psia} {R} {lbm/sec}

7/30 17:47 286 3393 3393 4 4 0.006 –0.05 29.69 0.00 2115.93 575.92 0.0 0.00E+00 2115.9 575.9 2.14E–03 0.00 –7.40 0.00 0.00 0.000 0.000

7/31 6:55 287 3394 3395 2 4 0.007 –0.03 29.69 0.00 2119.17 555.46 0.0 0.00E+00 2119.2 555.5 3.63E–04 0.00 49.70 0.00 0.00 0.000 0.000

7/31 7:21 287 3396 3397 5 4 0.011 –0.03 29.69 0.00 339.23 543.88 0.0 0.00E+00 339.2 543.9 3.63E+02 0.00 69.94 0.00 0.00 0.000 0.000

7/31 8:02 288 3398 3398 5 4 0.002 –0.03 40.17 0.00 778.03 594.92 2.4 9.98E+05 53.2 276.5 1.12E–04 214.57 –23.42 0.00 0.00 0.000 0.000

7/31 8:35 288 3399 3408 1 4 B4–A1 –0.03 40.17 0.00 777.88 594.50 2.4 1.00E+06 53.2 276.3 1.12E–04 214.53 –26.12 195.76 630.23 0.777 1.928

7/31 8:41 289 3409 3417 1 4 B4–A1 59.62 40.17 0.00 778.10 594.56 2.4 1.00E+06 53.2 276.3 1.12E–04 214.59 –26.30 195.86 631.05 0.778 1.932

7/31 8:47 290 3418 3426 1 4 B4–A1 120.39 40.17 0.00 778.10 594.58 2.4 1.00E+06 53.2 276.3 1.12E–04 214.59 –26.52 195.83 629.57 0.778 1.930

7/31 8:54 291 3427 3435 1 4 B4–A1 –179.95 40.17 0.00 778.06 594.75 2.4 9.99E+05 53.2 276.4 1.12E–04 214.58 –26.58 196.12 628.78 0.781 1.935

7/31 9:10 292 3436 3438 1 4 0.002 vary vary 0.00 777.89 594.50 2.4 1.00E+06 53.2 276.3 1.12E–04 214.53 –28.73 195.54 628.99 0.778 1.928

7/31 9:18 293 3439 3447 1 4 B4–A1 179.97 40.16 0.00 778.08 594.50 2.4 1.00E+06 53.2 276.3 1.12E–04 214.58 –29.02 98.91 623.07 0.380 0.941

7/31 9:23 294 3448 3456 1 4 B4–A1 120.37 40.16 0.00 778.06 594.90 2.4 9.99E+05 53.2 276.4 1.12E–04 214.58 –29.17 99.07 621.13 0.382 0.945

7/31 9:29 295 3457 3465 1 4 B4–A1 59.61 40.16 0.00 778.08 594.46 2.4 1.00E+06 53.2 276.2 1.12E–04 214.58 –29.29 99.21 621.13 0.383 0.947

7/31 9:33 296 3466 3474 1 4 B4–A1 –0.05 40.16 0.00 777.86 594.69 2.4 9.99E+05 53.2 276.3 1.12E–04 214.52 –29.51 98.97 621.00 0.382 0.944

7/31 9:46 297 3475 3478 1 4 0.047 vary vary 0.00 778.09 594.63 2.4 1.00E+06 53.2 276.3 1.12E–04 214.59 –29.47 295.57 630.36 1.192 2.951

7/31 10:30 298 3479 3487 1 4 B4–A1 0.01 40.16 0.00 1386.98 594.59 3.5 1.00E+06 18.2 172.3 6.15E–05 155.93 –21.37 142.97 621.87 0.563 1.915

7/31 10:35 299 3488 3496 1 4 B4–A1 59.57 40.16 0.00 1385.95 593.61 3.5 1.00E+06 18.2 172.1 6.15E–05 155.82 –19.93 143.04 620.88 0.565 1.919

7/31 11:06 300 3497 3505 1 4 B4–A1 120.37 40.16 0.00 1387.75 595.35 3.5 9.99E+05 18.2 172.6 6.14E–05 156.02 –24.02 143.07 620.01 0.565 1.914

7/31 11:10 301 3506 3514 1 4 B4–A1 179.95 40.16 0.00 1386.67 594.66 3.5 1.00E+06 18.2 172.4 6.14E–05 155.90 –22.11 143.49 619.90 0.567 1.923

7/31 11:20 302 3515 3523 1 4 B4–A1 179.95 40.16 0.00 1386.72 594.42 3.5 1.00E+06 18.2 172.3 6.15E–05 155.90 –21.32 71.21 614.77 0.266 0.905

7/31 11:24 303 3524 3532 1 4 B4–A1 120.43 40.16 0.00 1386.29 594.45 3.5 1.00E+06 18.2 172.3 6.15E–05 155.86 –21.17 70.78 612.99 0.264 0.898

7/31 11:29 304 3533 3541 1 4 B4–A1 59.59 40.16 0.00 1386.67 594.94 3.5 9.99E+05 18.2 172.4 6.14E–05 155.90 –21.08 71.07 612.72 0.266 0.904

7/31 11:34 305 3542 3550 1 4 B4–A1 –0.03 40.16 0.00 1387.22 595.11 3.5 9.99E+05 18.2 172.5 6.14E–05 155.96 –20.92 71.10 612.45 0.266 0.902

7/31 11:45 306 3551 3555 1 4 0.004 vary vary 0.00 1386.55 595.32 3.5 9.98E+05 18.2 172.6 6.14E–05 155.88 –18.81 vary 619.05 vary vary

7/31 12:22 307 3556 3564 1 4 B4–A1 0.05 40.17 0.00 3657.79 609.68 4.6 1.50E+06 11.2 116.5 5.58E–05 165.38 –7.60 151.93 618.38 0.602 1.923

7/31 12:27 308 3565 3573 5 4 B4–A1 59.98 40.17 0.00 3657.96 609.66 4.6 1.50E+06 11.2 116.5 5.58E–05 165.39 –8.93 148.34 618.86 0.605 1.920

7/31 12:34 309 3574 3582 1 4 B4–A1 59.53 40.17 0.00 3658.01 609.80 4.6 1.50E+06 11.2 116.6 5.58E–05 165.39 –10.11 151.99 619.74 0.601 1.921

7/31 12:48 310 3583 3592 1 4 B4–A1 120.36 40.17 0.00 3658.13 609.85 4.6 1.50E+06 11.2 116.6 5.58E–05 165.40 –10.79 152.14 620.37 0.601 1.922

7/31 12:54 311 3593 3601 1 4 B4–A1 –179.98 40.17 0.00 3657.77 609.71 4.6 1.50E+06 11.2 116.5 5.58E–05 165.38 –11.29 152.41 620.71 0.602 1.926

7/31 13:09 312 3602 3610 1 4 B4–A1 –179.97 40.17 0.00 3658.25 609.21 4.6 1.50E+06 11.2 116.4 5.59E–05 165.41 –11.47 76.81 615.87 0.285 0.915

7/31 13:14 313 3611 3619 1 4 B4–A1 120.39 40.17 0.00 3657.70 609.69 4.6 1.50E+06 11.2 116.5 5.58E–05 165.38 –13.52 76.48 614.91 0.287 0.918

7/31 13:19 314 3620 3628 1 4 B4–A1 59.63 40.17 0.00 3658.10 609.95 4.6 1.50E+06 11.2 116.6 5.58E–05 165.40 –13.53 76.47 614.87 0.286 0.916

7/31 13:25 315 3629 3637 1 4 B4–A1 0.05 40.17 0.00 3658.20 609.35 4.6 1.50E+06 11.2 116.5 5.59E–05 165.40 –12.03 76.39 614.81 0.285 0.912

Table B-3. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

142

RUN INFORMATION MODEL ATTITUDE & LOCATION RUN-AVERAGED FLOW CONDITIONS NOZZLE EXIT CONDITIONS

DATE TIME RUN POINT

Key # 

NOZ

PITCH ROLL X_STRUT Y_STRUT PTINF TTINF MACH REINF PINF TINF RHOINF QINF DEWPT PTJ TTJ WJ CT

2010 START END {deg} {deg} {in} {in} {psf} {R} {1/ft} {psf} {R} {slug/ft^3} {psf} {deg F} {psia} {R} {lbm/sec}

7/31 13:38 316 3638 3639 3 4 0.015 0.05 40.17 0.00 378.65 565.79 0.0 0.00E+00 378.6 565.8 3.90E–04 0.00 –25.91 0.00 0.00 0.000 0.000

7/31 13:40 316 3640 3640 3 4 0.016 0.05 40.17 0.00 2114.20 617.80 0.0 0.00E+00 2114.2 617.8 1.99E–03 0.00 –32.68 0.00 0.00 0.000 0.000

7/31 15:04 317 3641 3641 2 1 –0.051 60.98 40.17 0.00 2118.09 585.01 0.0 0.00E+00 2118.1 585.0 2.11E–03 0.00 6.80 0.00 0.00 0.000 0.000

7/31 15:22 317 3642 3644 2 1 –0.052 60.98 40.17 0.00 357.05 570.67 0.0 0.00E+00 357.0 570.7 3.64E–04 0.00 –18.77 0.00 0.00 0.000 0.000

7/31 15:50 318 3645 3649 1 1 vary 0.01 vary 0.00 777.90 594.64 2.4 9.99E+05 53.2 276.3 1.12E–04 214.53 –16.12 777.49 595.24 0.833 1.985

7/31 15:58 319 3650 3655 1 1 vary 0.01 vary 0.00 777.85 594.69 2.4 9.99E+05 53.2 276.3 1.12E–04 214.52 –16.04 193.57 593.31 0.189 0.457

7/31 16:20 320 3656 3660 1 1 vary 0.01 vary 0.00 1386.38 594.07 3.5 1.00E+06 18.2 172.2 6.15E–05 155.86 –10.20 563.49 605.49 0.589 1.957

7/31 16:43 321 3661 3666 1 1 vary 0.01 vary 0.00 3659.15 609.91 4.6 1.50E+06 11.2 116.6 5.58E–05 165.45 0.86 599.91 611.34 0.622 1.956

7/31 16:52 322 3667 3668 3 1 –0.012 –0.01 40.17 0.00 373.35 564.90 0.0 0.00E+00 373.4 564.9 3.85E–04 0.00 –7.83 0.00 0.00 0.000 0.000

7/31 16:55 322 3669 3669 3 1 –0.01 –0.01 40.17 0.00 2106.86 616.44 0.0 0.00E+00 2106.9 616.4 1.99E–03 0.00 –7.78 0.00 0.00 0.000 0.000

Key Run Condition

1 Normal Run

2 Pre-Run Wind-Off Zero

3 Post-Run Wind-Off Zero

4 Wind-Off Data Run or Checkout Run

5 Bad Data or Incorrect Operating Conditions

Table B-4. Angle of attack sweep schedule.

Pause 

Step

Schedule

A1 A2 A3

1 –8.0 –8.0 –8.0

2 –4.0 –4.0 –4.0

3 0.0 0.0 0.0

4 4.0 4.0 4.0

5 8.0 8.0 8.0

6 12.0 12.0 12.0

7 16.0 16.0

8 20.0 0.0

9 0.0

Table B-3. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

143

Table B-5. Statistical analysis of as-tested flow conditions.

(a) M = 2.40.

Parameter Units Min Max Median Mean Std Dev Std Err Mean

PT, lbf/ft2

774.360 780.840 777.816 777.844 0.58504 0.01813

TT, R 593.780 597.760 594.690 594.806 0.47827 0.01482

Dew Point deg F –29.559 –15.969 –24.624 –24.693 2.14019 0.06633

P lbf/ft2

52.966 53.409 53.202 53.204 0.04002 0.00124

T R 275.920 277.770 276.343 276.397 0.22224 0.00689

 slug/ft3

1.1154E–04 1.1260E–04 1.1215E–04 1.1214E–04 1.1463E–07 3.5528E–09

q lbf/ft2

213.558 215.345 214.511 214.519 0.16134 0.00500

V ft/sec 1954.350 1960.890 1955.840 1956.034 0.78602 0.02436

Re 1/ft 992577 1003361 999175 998983 1273.90520 39.48315

(b) M = 3.50.

Parameter Units Min Max Median Mean Std Dev Std Err Mean

PT, lbf/ft2

1375.270 1391.690 1386.720 1386.624 1.08953 0.04148

TT, R 592.710 596.540 594.700 594.677 0.54294 0.02067

Dew Point deg F –28.120 –9.414 –21.068 –20.351 3.14173 0.12022

P lbf/ft2

18.031 18.246 18.181 18.180 0.01428 0.00054

T R 171.800 172.910 172.377 172.370 0.15737 0.00599

 slug/ft3

6.0992E–05 6.1650E–05 6.1438E–05 6.1441E–05 6.8395E–08 2.6038E–09

q lbf/ft2

154.617 156.462 155.904 155.893 0.12249 0.00466

V ft/sec 2248.940 2256.200 2252.710 2252.671 1.02843 0.03915

Re 1/ft 992826 1004777 999558 999659.75 1502.36120 57.19392
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

144

Table B-5. Concluded.

(c) M = 4.60.

Parameter Units Min Max Median Mean Std Dev Std Err Mean

PT, lbf/ft2

3648.240 3660.980 3657.740 3657.843 0.83870 0.03326

TT, R 609.060 611.590 609.850 609.910 0.33981 0.01347

Dew Point deg F –20.624 1.131 –11.342 –10.480 2.85393 0.11317

P lbf/ft2

11.136 11.175 11.166 11.166 0.00256 0.00010

T R 116.411 116.894 116.562 116.573 0.06495 0.00258

 slug/ft3

5.5634E–05 5.5890E–05 5.5803E–05 5.5789E–05 3.3875E–08 1.3432E–09

q lbf/ft2

164.953 165.529 165.383 165.387 0.03792 0.00150

V ft/sec 2433.060 2438.110 2434.640 2434.755 0.67810 0.02689

Re 1/ft 1491902 1502623 1499140 1498914.4 1410.09850 55.91404
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

145

APPENDIX C

SCHLIEREN RESULTS

Schlieren videos were acquired with a high speed digital camera, the Vision Research Phantom 

12, to capture flow field dynamics resulting from jet/bow shock interactions. Due to data file 

storage constraints on the camera, only select test points within a run were captured to minimize 

the offload frequency. At times during the test when the camera storage was full, offloading of 

video files precluded capturing results for a few runs. Table C-1 provides a list of the schlieren 

videos captured in run chronological order, with an “X” to mark the specific angles of attack 

acquired. Also shown in Table C-1 are the video camera settings (camera resolution, framing 

rate, and total number of frames) for each run. The schlieren video cases are reorganized in

Table C-2 to provide the matrix of cases captured for each configuration: the baseline model, and 

center, tri- and quad-nozzle cases. All schlieren results are provided in run chronological order 

following the tables. In some cases, extra videos were taken with the model translated or rolled 

to reveal hidden flow features. These cases do not show up specifically in the tables, but the 

uniqueness of these repeat cases is contained within the figure captions. For the multi-nozzle 

cases, roll increments of 30 degrees (as opposed the standard 60 degrees called out in the run 

matrix) allowed for the three peripheral nozzles to be out of phase, thereby showing flow from 

each nozzle independently in the schlieren.

Flow dynamics are difficult to capture with a single extracted image from the video file. To 

better represent the unsteadiness, video processing was employed. For each case, three images 

are provided in a row to illustrate the level of flow unsteadiness. The first image provides a 

single arbitrary frame extracted from the video file, showing specific flow features frozen in 

time. The second image provides the average intensity of all frames from the video file. This 

particular type of processing is suggestive of schlieren video taken with standard video framing 

rates (30 fps), which tends to blur out unsteadiness and accentuates only steady features. The 

last image provides the standard deviation of all the frames in the video. In this case, the 

whiter/brighter areas indicate where the fluctuations are most intense, identifying regions of flow 

unsteadiness. When flow is steady, the three images will look similar, such as seen with the 

baseline cases. Note that video processing was applied consistently for all runs, the varying 

results with the first few runs were due to a schlieren knife edge misalignment that could not be 

compensated for with posttest digital enhancement.

For those interested in viewing the videos, they have been compiled into three files according to 

Mach number, each lasting just under 18 minutes. These videos have been archived at NASA 

YouTube Links:

 SRP_m2.4.avi: http://youtu.be/-ezb03W6KCc

 SRP_m3.5.avi: http://youtu.be/fTmPc1olhiU

 SRP_m4.6.avi: http://youtu.be/i-coJg_vgxI
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

146

Table C-1. Schlieren video acquisition information in run chronological order.

Run Nozzles Mach CT

Alpha, deg

Resolution

Framing Rate

# Frames

–8 –4 0 4 8 12 16 20 frames/sec

58 0 3.50 0.000 X X X X X X X 1280 x 800 6245 2471

67 0 3.50 0.000 X X X X X X X X 1280 x 800 6245 2471

86 0 4.60 0.000 X X X X X X X 1280 x 800 6245 2471

106 0 4.60 0.000 X X X X X X X X 1024 x 800 6245 3090

136 1 2.40 4.024 X X X 1024 x 800 6245 1390

137 1 2.40 3.002 X X X 1024 x 800 6245 1390

139 1 2.40 0.968 X X X X X 1024 x 800 6245 1390

141 1 2.40 1.982 X X X X 1024 x 800 6245 1390

150 1 3.50 2.978 X X X X 1024 x 800 6245 695

153 1 3.50 1.962 X X X X X 1024 x 800 6245 695

154 1 3.50 0.938 X X X X 1024 x 800 6245 695

157 1 3.50 0.448 X X X X 1024 x 800 6245 695

158 1 3.50 0.210 X X X X 1024 x 800 6245 695

163 1 4.60 2.959 X X X X 1024 x 800 6245 695

165 1 4.60 1.968 X X X X 1024 x 800 6245 695

167 1 4.60 0.943 X X X 1024 x 800 6245 695

169 1 4.60 0.454 X X 1024 x 800 6245 695

171 1 4.60 0.219 X 1024 x 800 6245 695

180 3 2.40 0.000 X X X X X X 896 x 704 5000 721

185 3 3.50 0.000 X X X X X X 896 x 704 5000 721

190 3 2.40 2.939 X X X X 896 x 704 5000 721

192 3 2.40 2.943 X 896 x 704 5000 721

194 3 2.40 1.940 X X X X 896 x 704 5000 721
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

147

Run Nozzles Mach CT

Alpha, deg

Resolution

Framing Rate

# Frames

–8 –4 0 4 8 12 16 20 frames/sec

198 3 2.40 0.944 X X X X 896 x 704 5000 721

202 3 2.40 0.431 X X X X 896 x 704 5000 721

206 3 2.40 0.435 X 896 x 704 5000 721

212 3 4.60 2.933 X X X X X 896 x 672 10000 598

214 3 4.60 2.954 X X X X X X X 896 x 672 10000 598

221 3 2.40 0.235 X X X 896 x 672 10000 598

222 3 3.50 2.963 X X X X X X 896 x 672 10000 598

225 3 3.50 2.985 X X X X X X 896 x 672 10000 598

226 3 3.50 1.956 X X X X 896 x 672 10000 598

247 3 4.60 1.919 X X X X X 896 x 672 10000 598

248 3 4.60 1.930 X X X X X 896 x 672 10000 598

249 3 4.60 0.898 X X X X 896 x 672 10000 598

253 3 4.60 0.428 X X X X 896 x 672 10000 598

257 3 4.60 0.199 X X X X 896 x 672 10000 598

262 3 4.60 2.937 X X X X 896 x 672 10000 598

263 3 4.60 2.935 X X X X 896 x 672 10000 598

264 3 4.60 vary X X 896 x 672 10000 598

265 3 3.50 0.912 X X X X 896 x 672 10000 598

266 3 3.50 0.830 X X X X 896 x 672 10000 598

267 3 3.50 vary X 896 x 672 10000 598

274 0 2.40 0.000 X X X X X X X X 896 x 672 10000 598

276 0 3.50 0.000 X X X X X X X X 896 x 672 10000 598

283 0 4.60 0.000 X X X X X X X X 896 x 672 10000 598

288 4 2.40 1.928 X X X X X X X X 896 x 672 10000 598

291 4 2.40 1.935 X X X X X X 896 x 672 10000 598

Table C-1. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

148

Run Nozzles Mach CT

Alpha, deg

Resolution

Framing Rate

# Frames

–8 –4 0 4 8 12 16 20 frames/sec

292 4 2.40 1.928 X 896 x 672 10000 598

293 4 2.40 0.941 X X X X X 896 x 672 10000 598

297 4 2.40 2.951 X 896 x 672 10000 598

298 4 3.50 1.915 X X X X 896 x 672 10000 598

301 4 3.50 1.923 X X X X 896 x 672 10000 598

305 4 3.50 0.902 X X X X 896 x 672 10000 598

306 4 3.50 vary X 896 x 672 10000 598

307 4 4.60 1.923 X X X X 896 x 672 10000 598

311 4 4.60 1.926 X X X X 896 x 672 10000 598

315 4 4.60 0.912 X X X X 896 x 672 10000 598

318 1 2.40 1.985 X X X 896 x 672 10000 598

319 1 2.40 0.457 X X X X X 896 x 672 10000 598

320 1 3.50 1.957 X X X 896 x 672 10000 598

321 1 4.60 1.956 X X X 896 x 672 10000 598

Table C-2. Schlieren cases rearranged by configuration.

(a) Matrix of baseline schlieren cases.

Mach 2.4 Mach 3.5 Mach 4.6

CT RUN

Alpha, deg

RUN

Alpha, deg

RUN

Alpha, deg

–8 –4 0 4 8 12 16 20 –8 –4 0 4 8 12 16 20 –8 –4 0 4 8 12 16 20

0.00 274 X X X X X X X X 58 X X X X X X X 86 X X X X X X X

67 X X X X X X X X 106 X X X X X X X X

276 X X X X X X X X 283 X X X X X X X X

Table C-1. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

149

Table C-2. Continued.

(b) Matrix of center nozzle schlieren cases.

Mach 2.4 Mach 3.5 Mach 4.6

CT RUN Alpha, deg RUN Alpha, deg RUN Alpha, deg

–8 –4 0 4 8 12 16 20 –8 –4 0 4 8 12 16 20 –8 –4 0 4 8 12 16 20

0

0.25 158 X X X X 171 X

0.5 319 X X X X X 157 X X X X 169 X X

1 139 X X X X X 154 X X X X 167 X X X

2 141 X X X X 320 X X X 321 X X X

3 318 X X X 153 X X X X X 165 X X X X

4 137 X X X 150 X X X X 163 X X X X

(c) Matrix of tri-nozzle schlieren cases.

Mach 2.4 Mach 3.5 Mach 4.6

CT RUN Alpha, deg RUN Alpha, deg RUN Alpha, deg

–8 –4 0 4 8 12 16 20 –8 –4 0 4 8 12 16 20 –8 –4 0 4 8 12 16 20

0 180 X X X X X X 185 X X X X X X

0.25 221 X X X 257 X X X X

0.5 202 X X X X 253 X X X X

0.5 206 X

1 265 X X X X 249 X X X X

1 198 X X X X 266 X X X X

2 194 X X X X 226 X X X X 247 X X X X X

2 248 X X X X X

3 190 X X X X 222 X X X X X X 212 X X X X X

3 192 X 225 X X X X X X 263 X X X X

3 262 X X X X

3 214 X X X X X X X

Vary 267 X 264 X X
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

150

Table C-2. Concluded.

(d) Matrix of quad-nozzle schlieren cases.

Mach 2.4 Mach 3.5 Mach 4.6

CT RUN

Alpha, deg

RUN

Alpha, deg

RUN

Alpha, deg

–8 –4 0 4 8 12 16 20 –8 –4 0 4 8 12 16 20 –8 –4 0 4 8 12 16 20

1 293 X X X X X 305 X X X X 315 X X X X

2 288 X X X X X X X X 298 X X X X 307 X X X X

2 291 X X X X X X 301 X X X X 311 X X X X

2 292 X

3 297 X

Vary 306 X
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

151

Single Image Average Intensity Standard Deviation

(a)  = –8 deg.

(b)  = –4 deg.

(c)  = 0 deg.

(d)  = 4 deg.

Figure C-1. Run 58: baseline schlieren video images for range of  at M∞ = 3.5, 

CT = 0.0, and φ = 60 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

152

Single Image Average Intensity Standard Deviation

(e)  = 8 deg.

(f)  = 12 deg.

(g)  = 20 deg.

Figure C-1. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = –8 deg.

Figure C-2. Run 67: baseline Schlieren video images for range of  at M∞ = 3.5, 

CT = 0.0, and φ= 60 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

153

Single Image Average Intensity Standard Deviation

(b)  = –4 deg.

(c)  = –0 deg.

(d)  = 4 deg.

(e)  = 8 deg. 

Figure C-2. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

154

Single Image Average Intensity Standard Deviation

(f)  = 12 deg.

(g)  = 16 deg.

(h)  = 20 deg.

Figure C-2. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = –8 deg.

Figure C-3. Run 86: baseline Schlieren video images for range of  at M∞ = 4.6, 

CT = 0.0, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

155

Single Image Average Intensity Standard Deviation

(b)  = –4 deg.

(c)  = 0 deg.

(d)  = 4 deg.

(e)  = 8 deg.

Figure C-3. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

156

Single Image Average Intensity Standard Deviation

(f)  = 12 deg.

(g)  = 16 deg.

Figure C-3. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = –8 deg.

(b)  = –4 deg.

Figure C-4. Run 106: baseline Schlieren video images for range of  at 

M∞ = 4.6, CT = 0.0, and φ = 120 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

157

Single Image Average Intensity Standard Deviation

(c)  = 0 deg.

(d)  = 4 deg.

(e)  = 8 deg.

(f)  = 12 deg.

Figure C-4. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

158

Single Image Average Intensity Standard Deviation

(g)  = 16 deg.

(h)  = 20 deg.

Figure C-4. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg, taken prior to the run with the model forward.

(b)  = 0 deg.

Figure C-5. Run 136: center nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 4.0, and φ= 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

159

Single Image Average Intensity Standard Deviation

(c)  = 4 deg.

(d)  = 12 deg. 

Figure C-5. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

Figure C-6. Run 137: center nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 3.0, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

160

Single Image Average Intensity Standard Deviation

(c)  = 12 deg. 

Figure C-6. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

(c)  = 8 deg.

Figure C-7. Run 139: center nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 1.0, and φ= 180 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

161

Single Image Average Intensity Standard Deviation

(d)  = 12 deg.

(e)  = 20 deg.

Figure C-7. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

Figure C-8. Run 141: center nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 2.0, and φ = 180 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

162

Single Image Average Intensity Standard Deviation

(c)  = 8 deg.

(d)  = 12 deg.

Figure C-8. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

Figure C-9. Run 150: center nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 3.0, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

163

Single Image Average Intensity Standard Deviation

(c)  = 12 deg.

(d)  = 20 deg. 

Figure C-9. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

Figure C-10. Run 153: center nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 2.0, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

164

Single Image Average Intensity Standard Deviation

(c)  = 8 deg.

(d)  = 12 deg.

(e)  = 20 deg.

Figure C-10. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-11. Run 154: center nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 1.0, and φ= 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

165

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

(c)  = 12 deg.

d)  = 20 deg.

Figure C-11. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-12. Run 157: center nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 0.5, and φ= 0 deg. 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

166

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

c)  = 12 deg.

(d)  = 20 deg.

Figure C-12. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-13. Run 158: center nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 0.2, and φ= 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

167

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

(c)  = 12 deg.

(d)  = 20 deg.

Figure C-13. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-14. Run 163: center nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 3.0, and φ= 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

168

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

(c)  = 12 deg.

(d)  = 20 deg.

Figure C-14. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C- 15. Run 165: center nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 2.0, and φ =deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

169

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

(c)  = 12 deg.

(d)  = 20 deg.

Figure C-15. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-16. Run 167: center nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 1.0, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

170

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

(c)  = 12 deg.

Figure C-16. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

Figure C-17. Run 169: center nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 0.5, and φ = 180 deg. 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

171

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-18. Run 171: center nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 0.2, and φ =180 deg.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

(c)  = 8 deg.

Figure C-19. Run 180: tri-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 0.0, and φ = deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

172

Single Image Average Intensity Standard Deviation

(d)  = 12 deg.

(e)  = 16 deg.

(f)  = 20 deg.

Figure C-19. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-20. Run 185: tri-nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 0.0, and φ= deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

173

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

(c)  = 8 deg.

(d)  = 12 deg.

(e)  = 16 deg.

Figure C-20. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

174

Single Image Average Intensity Standard Deviation

(f)  = 20 deg.

Figure C-20. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

(c)  = 12 deg.

Figure C-21. Run 190: tri-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 3.0, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

175

Single Image Average Intensity Standard Deviation

(d)  = 20 deg.

Figure C-21. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 8 deg.

Figure C-22. Run 192: tri-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 3.0, and φ= 120deg.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-23. Run 194: tri-nozzle schlieren video images for range of  at M∞ =

2.4, CT = 2.0, and φ = 180 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

176

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

(c) = 12 deg.

(d)  = 20 deg.

Figure C-23. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-24. Run 198: tri-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 1.0, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

177

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

(c)  = 12 deg.

(d)  = 20 deg.

Figure C-24. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-25. Run 202: tri-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 0.43, and φ = 180 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

178

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

(c)  = 12 deg.

(d)  = 20 deg.

Figure C-25. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-26. Run 206: tri-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 0.43, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

179

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

(c)  = 8 deg.

(d)  = 12 deg.

Figure C-27. Run 212: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 2.93, and φ = 60 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

180

Single Image Average Intensity Standard Deviation

(e)  = 16 deg.

Figure C-27. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = –8 deg.

(b)  = –4 deg.

(c)  = 0 deg.

Figure C-28. Run 214: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 2.95, and φ = 180 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

181

Single Image Average Intensity Standard Deviation

(d)  = 4 deg.

(e)  = 8 deg.

(f)  = 12 deg.

(g)  = 16 deg.

Figure C-28. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

182

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

(c)  = 12 deg.

Figure C-29. Run 221: tri-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 0.24, and φ = 0 deg.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-30. Run 222: tri-nozzle schlieren video images for range of  at M∞ =

3.5, CT = 2.96, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

183

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

c)  = 8 deg.

(d)  = 12 deg.

(e)  = 16 deg.

Figure C-30. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

184

Single Image Average Intensity Standard Deviation

(f)  = 20 deg.

Figure C-30. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

c)  = 8 deg.

Figure C-31. Run 225: tri-nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 2.99, and φ = 180 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

185

Single Image Average Intensity Standard Deviation

(d)  = 12 deg.

(e)  = 16 deg.

(f)  = 20 deg.

Figure C-31. Concluded.

Single Image Average Intensity Standard Deviation

a)  = 0 deg.

Figure C-32. Run 226: tri-nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 1.96, and φ= 180 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

186

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

(c)  = 12 deg.

(d)  = 20 deg.

Figure C-32. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-33. Run 247: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 1.92, and φ= 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

187

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

(c)  = 8 deg.

(d)  = 12 deg.

(e)  = 20 deg.

Figure C-33. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

188

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

(c)  = 8 deg.

(d)  = 12 deg.

Figure C-34. Run 248: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 1.93, and φ = 180 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

189

Single Image Average Intensity Standard Deviation

(e)  = 20 deg.

Figure C-34. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

(c)  = 12 deg.

Figure C-35. Run 249: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 0.90, and φ= 180 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

190

Single Image Average Intensity Standard Deviation

(d)  = 20 deg.

Figure C-35. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

(c)  = 12 deg.

Figure C-36. Run 253: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 0.43, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

191

Single Image Average Intensity Standard Deviation

(d)  = 20 deg.

Figure C-36. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

(c)  = 12 deg.

Figure C-37. Run 257: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 0.20, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

192

Single Image Average Intensity Standard Deviation

(d)  = 16 deg.

Figure C-37. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

(c)  = 12 deg.

Figure C-38. Run 262: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 2.94, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

193

Single Image Average Intensity Standard Deviation

(d)  = 16 deg.

Figure C-38. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

(c)  = 12 deg.

Figure C-39. Run 263: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 2.94, and φ = 180deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

194

Single Image Average Intensity Standard Deviation

(d)  = 16deg.

Figure C-39. Concluded.

Single Image Average Intensity Standard Deviation

(a) CT = 3.

(b) CT = 4.

(c) CT = 5.

Figure C-40. Run 264: tri-nozzle schlieren video images for range of  at 

M∞ = 4.6,  = 0 deg, and φ = 60 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

195

Single Image Average Intensity Standard Deviation

(d) CT = 6.

Figure C-40. Concluded.

Single Image Average Intensity Standard Deviation

(a) CT = 3.

Figure C-41. Run 264: tri-nozzle schlieren video images for range of  at M∞ = 4.6, 

 = 12 deg, and φ = 60 deg.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-42. Run 265: tri-nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 0.91, and φ= 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

196

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

(c)  = 12 deg.

(d)  = 20 deg.

Figure C-42. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-43. Run 266: tri-nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 0.83, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

197

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

(c)  = 12 deg.

(d)  = 20 deg.

Figure C-43. Concluded.

Single Image Average Intensity Standard Deviation

(a) CT = 4, XS = 40”, and φ= 0 deg.

Figure C-44. Run 267: tri-nozzle schlieren video images for range of  at 

M∞ = 3.5 and  = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

198

Single Image Average Intensity Standard Deviation

(b) CT = 5, XS = 40”, and φ= 0 deg.

(c) CT = 5, XS = 40”, and φ= 30 deg.

(d) CT = 5, XS = 42”, and φ= 30 deg.

(e) CT = 5, XS = 42”, and φ= 0 deg.

Figure C-44. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

199

Single Image Average Intensity Standard Deviation

(f) CT = 6, XS = 40”, and φ= 0 deg.

(g) CT = 6, XS = 40”, and φ= 30 deg.

(h) CT = 6, XS = 44”, and φ= 30 deg.

(i) CT = 6, XS = 44”, and φ= 0 deg.

Figure C-44. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

200

Single Image Average Intensity Standard Deviation

(a)  = –8 deg.

(b)  = –4 deg.

(c)  = 0 deg.

(d)  = 4 deg.

Figure C-45. Run 274: baseline schlieren video images for range of  at 

M∞ = 2.4, CT = 0.0, and φ = 180 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

201

Single Image Average Intensity Standard Deviation

(e)  = 8 deg.

(f)  = 12 deg.

(g)  = 16 deg.

(h)  = 20 deg.

Figure C-45. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

202

Single Image Average Intensity Standard Deviation

(a)  = –8 deg.

(b)  = –4 deg.

(c)  = 0 deg.

(d)  = 4 deg.

Figure C-46. Run 276: baseline schlieren video images for range of  at 

M∞ = 3.5, CT = 0.0, and φ= 180 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

203

Single Image Average Intensity Standard Deviation

(e)  = 8 deg.

(f)  = 12 deg.

(g)  = 16 deg.

(h)  = 20 deg.

Figure C-46. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

204

Single Image Average Intensity Standard Deviation

(a)  = –8 deg.

(b)  = –4 deg.

(c)  = 0 deg.

(d)  = 4 deg.

Figure C-47. Run 283: baseline schlieren video images for range of  at 

M∞ = 4.6, CT = 0.0, and φ = 180 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

205

Single Image Average Intensity Standard Deviation

(e)  = 8 deg.

(f)  = 12 deg.

(g)  = 16 deg.

(h)  = 20 deg.

Figure C-47. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

206

Single Image Average Intensity Standard Deviation

(a)  = –8 deg.

(b)  = –4 deg.

(c)  = 0 deg.

(d)  = 4 deg.

Figure C-48. Run 288: quad-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 1.93, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

207

Single Image Average Intensity Standard Deviation

(e)  = 8 deg.

(f)  = 12 deg.

(g)  = 16 deg.

(h)  = 20 deg.

Figure C-48. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

208

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

(c)  = 8 deg.

(d)  = 12 deg.

Figure C-49. Run 291: quad-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 1.94, and φ = 180 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

209

Single Image Average Intensity Standard Deviation

(e)  = 16 deg.

(f)  = 20 deg.

Figure C-49. Concluded.

Single Image Average Intensity Standard Deviation

(a) XS = 40” and φ= 180 deg.

(b) XS = 42” and φ= 180 deg.

Figure C-50. Run 292: quad-nozzle schlieren video images for range of model 

positions at M∞ = 2.4,  = 0 deg, and CT = 1.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

210

Single Image Average Intensity Standard Deviation

(c) XS = 42” and φ= 150 deg.

Figure C-50. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

(c)  = 8 deg.

Figure C-51. Run 293: quad-nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 0.94, and φ = 180 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

211

Single Image Average Intensity Standard Deviation

(d)  = 12 deg.

(e)  = 20 deg.

Figure C-51. Concluded.

Single Image Average Intensity Standard Deviation

(a) XS = 40” and φ= 0 deg.

(b) XS = 40” and φ= 30 deg.

Figure C-52. Run 297: quad-nozzle schlieren video images for range of model 

positions at M∞ = 2.4,  = 0 deg, and CT = 2.95. 
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

212

Single Image Average Intensity Standard Deviation

(c) XS = 43” and φ= 30deg.

(d) XS = 43” and φ= 0 deg.

Figure C-52. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

Figure C-53. Run 298: quad-nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 1.91, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

213

Single Image Average Intensity Standard Deviation

(c)  = 12 deg.

(d)  = 20 deg.

Figure C-53. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

Figure C-54. Run 301: quad-nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 1.92, and φ = 180 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

214

Single Image Average Intensity Standard Deviation

(c)  = 12 deg.

(d)  = 20 deg.

Figure C-54. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

Figure C-55. Run 305: quad-nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 0.90, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

215

Single Image Average Intensity Standard Deviation

(c)  = 12 deg.

(d)  = 20 deg.

Figure C-55. Concluded.

Single Image Average Intensity Standard Deviation

(a) XS = 41”, CT = 2, and φ=  deg.

(b) XS = 40”, CT = 3, and φ= 0 deg.

Figure C-56. Run 306: quad-nozzle schlieren video images for range of model 

positions at M∞ = 3.5 and  = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

216

Single Image Average Intensity Standard Deviation

(c) XS = 40”, CT = 3, and φ= 30 deg.

(d) XS = 43”, CT = 3, and φ= 30deg.

(e) XS = 43”, CT = 3, and φ= 0 deg.

Figure C-56. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-57. Run 307: quad-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 1.92, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

217

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

(c)  = 12 deg.

(d)  = 20 deg.

Figure C-57. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-58. Run 311: quad-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 1.93, and φ = 180 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

218

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

(c)  = 12 deg.

(d)  = 20 deg.

Figure C-58. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

Figure C-59. Run 315: quad-nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 0.91, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

219

Single Image Average Intensity Standard Deviation

(b)  = 4 deg.

(c)  = 12 deg.

(d)  = 20 deg.

Figure C-59. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg, XS = 40”.

Figure C-60. Run 318: center nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 1.98, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

220

Single Image Average Intensity Standard Deviation

(b)  = 0 deg, XS = 44”.

(c)  = 8 deg, XS = 40”.

(d)  = 8 deg, XS = 43”.

(e)  = 12 deg, XS = 40”.

Figure C-60. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

221

Single Image Average Intensity Standard Deviation

(a)  = 0 deg.

(b)  = 4 deg.

(c)  = 8 deg.

(d)  = 12 deg.

Figure C-61. Run 319: center nozzle schlieren video images for range of  at 

M∞ = 2.4, CT = 0.46, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

222

Single Image Average Intensity Standard Deviation

(e)  = 12 deg, XS = 40”.

(f)  = 20 deg.

Figure C-61. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg, XS = 40”.

(b)  = 0 deg, XS = 43”.

Figure C-62. Run 320: center nozzle schlieren video images for range of  at 

M∞ = 3.5, CT = 1.96, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

223

Single Image Average Intensity Standard Deviation

(c)  = 8 deg, XS = 40”.

(d)  = 8 deg, XS = 43”.

(e)  = 12 deg, XS = 40”.

Figure C-62. Concluded.

Single Image Average Intensity Standard Deviation

(a)  = 0 deg, XS = 40”.

Figure C-63. Run 321: center nozzle schlieren video images for range of  at 

M∞ = 4.6, CT = 1.96, and φ = 0 deg.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

224

Single Image Average Intensity Standard Deviation

(b)  = 0 deg, XS = 43”.

(c)  = 8 deg, XS = 40”.

(d)  = 8 deg, XS = 43”.

(e)  = 12 deg, XS = 40”.

Figure C-63. Continued.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

225

Single Image Average Intensity Standard Deviation

(f)  = 12 deg, XS = 43”.

Figure C-63. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

226

APPENDIX D

PRESSURE DATA LINE PLOTS

Plots of the pressure coefficients for selected pressure ports are given for each run performed 

during the wind tunnel experiment, with the exception of the six runs listed below. For each run, 

individual plots are provided for the both the forebody and aft body of the model at nominal 

angles of attack of –8, –4, 0, 4, 8, 12, 16, and 20 degrees, and labeled a–h, respectively, with the 

actual model angle of attack shown to the right of the label. The pressure coefficient data are 

plotted with respect to the cylindrical model coordinate system illustrated at the top of each page. 

Results are shown for arrays of pressure ports at six different azimuthal orientations around the 

body, as illustrated in the diagram and listed in the key at the upper right. These azimuths were 

chosen to provide good coverage of the forebody and because the azimuths are common to both 

the forebody and aft body. Note that there are no pressure ports on the aft body at the  = 60° 

azimuth, however. Runs 292, 297, 306, 319, 320, and 321 were mainly repeat runs completed 

for the sake of obtaining additional schlieren locations and roll angles and, thus, did not follow 

the normal angle of attack sweep.

The plots are presented with one range of Cp on the ordinate for the aft body and four ranges of 

Cp on the ordinate for the forebody. The plot ordinate range on the forebody was chosen based 

on the maximum Cp values for a given model configuration and thrust coefficient. No error bars 

are shown to avoid cluttering the small plots. Information on the Cp uncertainties is provided in 

the main body of the paper. The model configuration is given in the information string at the 

bottom of each page and is also shown in the diagram at the upper left of each page. The four 

smaller circles within the forebody diagram represent the four nozzles, with a filled circle 

representing a powered nozzle for that particular run.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

227

Figure D-1. Baseline configuration, Run 013, M∞ = 2.4, Re∞ = 1.0x106/ft, φ

= 0.03°, XS = 25.16 in, YS = 0.03 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

228

Figure D-1. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

229

Figure D-2. Baseline configuration, Run 014, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.97°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

230

Figure D-2. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

231

Figure D-3. Baseline configuration, Run 016, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

232

Figure D-3. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

233

Figure D-4. Baseline configuration, Run 017, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 59.86°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

234

Figure D-4. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

235

Figure D-5. Baseline configuration, Run 018, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.96°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

236

Figure D-5. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

237

Figure D-6. Baseline configuration, Run 019, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.91°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

238

Figure D-6. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

239

Figure D-7. Baseline configuration, Run 020, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 39.93 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

240

Figure D-7. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

241

Figure D-8. Baseline configuration, Run 021, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 59.88°, XS = 39.93 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

242

Figure D-8. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

243

Figure D-9. Baseline configuration, Run 022, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 120.06°, XS = 39.93 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

244

Figure D-9. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

245

Figure D-10. Baseline configuration, Run 023, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 39.93 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

246

Figure D-10. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

247

Figure D-11. Baseline configuration, Run 024, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 39.93 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

248

Figure D-11. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

249

Figure D-12. Baseline configuration, Run 025, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.08°, XS = 39.93 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

250

Figure D-12. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

251

Figure D-13. Baseline configuration, Run 026, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.03°, XS = 50.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

252

Figure D-13. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

253

Figure D-14. Baseline configuration, Run 027, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.08°, XS = 50.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

254

Figure D-14. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

255

Figure D-15. Baseline configuration, Run 028, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 120.06°, XS = 50.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

256

Figure D-15. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

257

Figure D-16. Baseline configuration, Run 029, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.91°, XS = 50.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

258

Figure D-16. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

259

Figure D-17. Baseline configuration, Run 030, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.91°, XS = 25.18 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

260

Figure D-17. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

261

Figure D-18. Baseline configuration, Run 031, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.92°, XS = 25.18 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

262

Figure D-18. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

263

Figure D-19. Baseline configuration, Run 032, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 25.18 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

264

Figure D-19. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

265

Figure D-20. Baseline configuration, Run 033, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 25.18 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

266

Figure D-20. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

267

Figure D-21. Baseline configuration, Run 034, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 25.18 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

268

Figure D-21. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

269

Figure D-22. Baseline configuration, Run 035, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.08°, XS = 25.18 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

270

Figure D-22. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

271

Figure D-23. Baseline configuration, Run 036, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.90°, XS = 25.18 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

272

Figure D-23. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

273

Figure D-24. Baseline configuration, Run 037, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 25.18 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

274

Figure D-24. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

275

Figure D-25. Baseline configuration, Run 038, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.19 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

276

Figure D-25. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

277

Figure D-26. Baseline configuration, Run 039, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.90°, XS = 40.19 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

278

Figure D-26. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

279

Figure D-27. Baseline configuration, Run 040, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.92°, XS = 40.19 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

280

Figure D-27. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

281

Figure D-28. Baseline configuration, Run 041, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 40.19 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

282

Figure D-28. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

283

Figure D-29. Baseline configuration, Run 042, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.19 in, YS = −8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

284

Figure D-29. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

285

Figure D-30. Baseline configuration, Run 043, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.92°, XS = 40.19 in, YS = −8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

286

Figure D-30. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

287

Figure D-31. Baseline configuration, Run 044, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.90°, XS = 40.19 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

288

Figure D-31. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

289

Figure D-32. Baseline configuration, Run 045, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.19 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

290

Figure D-32. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

291

Figure D-33. Baseline configuration, Run 046, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 50.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

292

Figure D-33. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

293

Figure D-34. Baseline configuration, Run 047, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.98°, XS = 50.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

294

Figure D-34. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

295

Figure D-35. Baseline configuration, Run 048, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 50.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

296

Figure D-35. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

297

Figure D-36. Baseline configuration, Run 049, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 50.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

298

Figure D-36. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

299

Figure D-37. Baseline configuration, Run 050, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.96°, XS = 50.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

300

Figure D-37. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

301

Figure D-38. Baseline configuration, Run 051, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.94°, XS = 50.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

302

Figure D-38. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

303

Figure D-39. Baseline configuration, Run 052, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 50.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

304

Figure D-39. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

305

Figure D-40. Baseline configuration, Run 053, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 39.93 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

306

Figure D-40. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

307

Figure D-41. Baseline configuration, Run 054, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.06°, XS = 40.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

308

Figure D-41. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

309

Figure D-42. Baseline configuration, Run 055, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

310

Figure D-42. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

311

Figure D-43. Baseline configuration, Run 056, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.07°, XS = 40.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

312

Figure D-43. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

313

Figure D-44. Baseline configuration, Run 057, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.07°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

314

Figure D-44. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

315

Figure D-45. Baseline configuration, Run 058, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.98°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

316

Figure D-45. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

317

Figure D-46. Baseline configuration, Run 059, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 120.12°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

318

Figure D-46. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

319

Figure D-47. Baseline configuration, Run 060, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

320

Figure D-47. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

321

Figure D-48. Baseline configuration, Run 065, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.01°, XS = 25.16 in, YS = −8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

322

Figure D-48. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

323

Figure D-49. Baseline configuration, Run 067, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 60.00°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

324

Figure D-49. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

325

Figure D-50. Baseline configuration, Run 068, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.02°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

326

Figure D-50. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

327

Figure D-51. Baseline configuration, Run 069, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 179.95°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

328

Figure D-51. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

329

Figure D-52. Baseline configuration, Run 070, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

330

Figure D-52. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

331

Figure D-53. Baseline configuration, Run 073, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.98°, XS = 40.18 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

332

Figure D-53. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

333

Figure D-54. Baseline configuration, Run 074, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.96°, XS = 40.18 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

334

Figure D-54. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

335

Figure D-55. Baseline configuration, Run 075, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.03°, XS = 40.18 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

336

Figure D-55. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

337

Figure D-56. Baseline configuration, Run 076, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 0.03°, XS = 40.18 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

338

Figure D-56. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

339

Figure D-57. Baseline configuration, Run 077, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.93°, XS = 40.16 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

340

Figure D-57. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

341

Figure D-58. Baseline configuration, Run 078, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.98°, XS = 40.16 in, YS = 7.95 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

342

Figure D-58. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

343

Figure D-59. Baseline configuration, Run 079, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −179.99°, XS = 40.16 in, YS = 7.95 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

344

Figure D-59. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

345

Figure D-60. Baseline configuration, Run 080, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −179.99°, XS = 50.15 in, YS = 7.95 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

346

Figure D-60. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

347

Figure D-61. Baseline configuration, Run 081, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 119.98°, XS = 50.15 in, YS = 7.95 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

348

Figure D-61. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

349

Figure D-62. Baseline configuration, Run 082, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.94°, XS = 50.15 in, YS = 7.95 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

350

Figure D-62. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

351

Figure D-63. Baseline configuration, Run 083, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 0.01°, XS = 50.15 in, YS = 7.95 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

352

Figure D-63. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

353

Figure D-64. Baseline configuration, Run 086, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 0.01°, XS = 25.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

354

Figure D-64. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

355

Figure D-65. Baseline configuration, Run 087, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 59.98°, XS = 25.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

356

Figure D-65. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

357

Figure D-66. Baseline configuration, Run 088, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 119.96°, XS = 25.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

358

Figure D-66. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

359

Figure D-67. Baseline configuration, Run 089, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 179.91°, XS = 25.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

360

Figure D-67. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

361

Figure D-68. Baseline configuration, Run 090, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

362

Figure D-68. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

363

Figure D-69. Baseline configuration, Run 091, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 59.94°, XS = 40.18 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

364

Figure D-69. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

365

Figure D-70. Baseline configuration, Run 092, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 119.98°, XS = 40.18 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

366

Figure D-70. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

367

Figure D-71. Baseline configuration, Run 093, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 179.91°, XS = 40.18 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

368

Figure D-71. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

369

Figure D-72. Baseline configuration, Run 094, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 179.91°, XS = 50.14 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

370

Figure D-72. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

371

Figure D-73. Baseline configuration, Run 095, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 119.96°, XS = 50.14 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

372

Figure D-73. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

373

Figure D-74. Baseline configuration, Run 096, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 59.90°, XS = 50.14 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

374

Figure D-74. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

375

Figure D-75. Baseline configuration, Run 097, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = −0.07°, XS = 50.14 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

376

Figure D-75. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

377

Figure D-76. Baseline configuration, Run 098, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = −0.07°, XS = 50.14 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

378

Figure D-76. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

379

Figure D-77. Baseline configuration, Run 099, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 59.86°, XS = 50.14 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

380

Figure D-77. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

381

Figure D-78. Baseline configuration, Run 100, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 120.06°, XS = 50.14 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

382

Figure D-78. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

383

Figure D-79. Baseline configuration, Run 101, M∞ = 4.6, Re∞ = 1.1x107/ft, 

φ = 179.97°, XS = 50.14 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

384

Figure D-80. Baseline configuration, Run 104, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.03°, XS = 25.19 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

385

Figure D-80. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

386

Figure D-81. Baseline configuration, Run 105, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.94°, XS = 25.19 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

387

Figure D-81. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

388

Figure D-82. Baseline configuration, Run 106, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.02°, XS = 25.19 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

389

Figure D-82. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

390

Figure D-83. Baseline configuration, Run 107, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.93°, XS = 25.19 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

391

Figure D-83. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

392

Figure D-84. Baseline configuration, Run 108, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.93°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

393

Figure D-84. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

394

Figure D-85. Baseline configuration, Run 109, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 119.98°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

395

Figure D-85. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

396

Figure D-86. Baseline configuration, Run 110, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.88°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

397

Figure D-86. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

398

Figure D-87. Baseline configuration, Run 111, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.01°, XS = 40.09 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

399

Figure D-87. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

400

Figure D-88. Baseline configuration, Run 112, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.01°, XS = 50.19 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

401

Figure D-88. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

402

Figure D-89. Baseline configuration, Run 113, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.96°, XS = 50.19 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

403

Figure D-89. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

404

Figure D-90. Baseline configuration, Run 114, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.10°, XS = 50.19 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

405

Figure D-90. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

406

Figure D-91. Baseline configuration, Run 115, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.97°, XS = 50.19 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

407

Figure D-91. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

408

Figure D-92. Baseline configuration, Run 116, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.97°, XS = 50.19 in, YS = 8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

409

Figure D-92. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

410

Figure D- 93. Baseline configuration, Run 117, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 119.98°, XS = 50.19 in, YS = 8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

411

Figure D-93. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

412

Figure D-94. Baseline configuration, Run 118, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.90°, XS = 50.19 in, YS = 8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

413

Figure D-94. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

414

Figure D-95. Baseline configuration, Run 119, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.03°, XS = 50.19 in, YS = 8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

415

Figure D-95. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

416

Figure D-96. Baseline configuration, Run 120, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.03°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

417

Figure D-96. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

418

Figure D-97. Baseline configuration, Run 121, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 60.00°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

419

Figure D-97. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

420

Figure D-98. Baseline configuration, Run 122, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.06°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

421

Figure D-98. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

422

Figure D-99. Baseline configuration, Run 123, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.93°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

423

Figure D-99. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

424

Figure D-100. Center nozzle configuration, Run 136, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.01°, XS = 40.16 in, YS = 0.00 in, CT = 3.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

425

Figure D-100.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

426

Figure D-101. Center nozzle configuration, Run 137, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 3.01.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

427

Figure D-101.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

428

Figure D-102. Center nozzle configuration, Run 138, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 3.02.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

429

Figure D-102.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

430

Figure D-103. Center nozzle configuration, Run 139, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 0.97.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

431

Figure D-103.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

432

Figure D-104. Center nozzle configuration, Run 140, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.97.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

433

Figure D-104.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

434

Figure D-105. Center nozzle configuration, Run 141, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 1.98.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

435

Figure D-105.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

436

Figure D-106. Center nozzle configuration, Run 142, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.91°, XS = 40.15 in, YS = 0.00 in, CT = 1.97.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

437

Figure D-106.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

438

Figure D-107. Center nozzle configuration, Run 143, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.91°, XS = 40.15 in, YS = 0.00 in, CT = 0.47.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

439

Figure D-107.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

440

Figure D-108. Center nozzle configuration, Run 144, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.46.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

441

Figure D-108.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

442

Figure D-109. Center nozzle configuration, Run 145, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.23.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

443

Figure D-109.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

444

Figure D-110. Center nozzle configuration, Run 146, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.23.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

445

Figure D-110.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

446

Figure D-111. Center nozzle configuration, Run 148, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

447

Figure D-111.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

448

Figure D-112. Center nozzle configuration, Run 149, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

449

Figure D-112.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

450

Figure D-113. Center nozzle configuration, Run 150, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.03°, XS = 40.17 in, YS = 0.00 in, CT = 2.99.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

451

Figure D-113.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

452

Figure D-114. Center nozzle configuration, Run 151, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −179.97°, XS = 40.17 in, YS = 0.00 in, CT = 2.98.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

453

Figure D-114.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

454

Figure D-115. Center nozzle configuration, Run 152, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −179.97°, XS = 40.17 in, YS = 0.00 in, CT = 1.97.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

455

Figure D-115.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

456

Figure D-116. Center nozzle configuration, Run 153, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.09°, XS = 40.17 in, YS = 0.00 in, CT = 1.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

457

Figure D-116.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

458

Figure D-117. Center nozzle configuration, Run 154, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.09°, XS = 40.17 in, YS = 0.00 in, CT = 0.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

459

Figure D-117.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

460

Figure D-118. Center nozzle configuration, Run 155, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 179.91°, XS = 40.17 in, YS = 0.00 in, CT = 0.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

461

Figure D-118.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

462

Figure D-119. Center nozzle configuration, Run 156, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 179.93°, XS = 40.17 in, YS = 0.00 in, CT = 0.46.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

463

Figure D-119.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

464

Figure D-120. Center nozzle configuration, Run 157, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.07°, XS = 40.17 in, YS = 0.00 in, CT = 0.45.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

465

Figure D-120.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

466

Figure D-121. Center nozzle configuration, Run 159, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.01°, XS = 40.17 in, YS = 0.00 in, CT = 0.21.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

467

Figure D-121.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

468

Figure D-122. Center nozzle configuration, Run 160, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.93°, XS = 40.17 in, YS = 0.00 in, CT = 0.21.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

469

Figure D-122.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

470

Figure D-123. Center nozzle configuration, Run 161, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.93°, XS = 40.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

471

Figure D-123.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

472

Figure D-124. Center nozzle configuration, Run 162, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.03°, XS = 40.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

473

Figure D-124.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

474

Figure D-125. Center nozzle configuration, Run 163, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.03°, XS = 40.17 in, YS = 0.00 in, CT = 2.97.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

475

Figure D-125.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

476

Figure D-126. Center nozzle configuration, Run 164, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.93°, XS = 40.17 in, YS = 0.00 in, CT = 2.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

477

Figure D-126.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

478

Figure D-127. Center nozzle configuration, Run 165, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.93°, XS = 40.15 in, YS = 0.00 in, CT = 1.98.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

479

Figure D-127.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

480

Figure D-128. Center nozzle configuration, Run 166, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.03°, XS = 40.15 in, YS = 0.00 in, CT = 1.97.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

481

Figure D-128.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

482

Figure D-129. Center nozzle configuration, Run 167, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

483

Figure D-129.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

484

Figure D-130. Center nozzle configuration, Run 168, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

485

Figure D-130.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

486

Figure D-131. Center nozzle configuration, Run 169, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.46.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

487

Figure D-131.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

488

Figure D-132. Center nozzle configuration, Run 170, M∞ = 4.6, Re∞ = 1.5x107/ft,

φ = 0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.46.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

489

Figure D-132.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

490

Figure D-133. Center nozzle configuration, Run 171, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.22.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

491

Figure D-133.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

492

Figure D-134. Center nozzle configuration, Run 172, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.91°, XS = 40.15 in, YS = 0.00 in, CT = 0.22.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

493

Figure D-134.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

494

Figure D-135. Center nozzle configuration, Run 173, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.91°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

495

Figure D-135.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

496

Figure D-136. Center nozzle configuration, Run 174, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.07°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

497

Figure D-1361. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

498

Figure D-137.Tri-nozzle configuration, Run 180, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

499

Figure D-137.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

500

Figure D-138.Tri-nozzle configuration, Run 181, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

501

Figure D-138.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

502

Figure D-139.Tri-nozzle configuration, Run 182, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 120.02°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

503

Figure D-139.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

504

Figure D-140.Tri-nozzle configuration, Run 183, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

505

Figure D-140.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

506

Figure D-141.Tri-nozzle configuration, Run 184, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

507

Figure D-141.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

508

Figure D-142.Tri-nozzle configuration, Run 185, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.88°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

509

Figure D-142.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

510

Figure D-143.Tri-nozzle configuration, Run 186, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 120.00°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

511

Figure D-143.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

512

Figure D-144.Tri-nozzle configuration, Run 187, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

513

Figure D-144.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

514

Figure D-145.Tri-nozzle configuration, Run 190, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 2.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

515

Figure D-145.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

516

Figure D-146.Tri-nozzle configuration, Run 191, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.88°, XS = 40.15 in, YS = 0.00 in, CT = 2.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

517

Figure D-146.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

518

Figure D-147.Tri-nozzle configuration, Run 192, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 120.00°, XS = 40.15 in, YS = 0.00 in, CT = 2.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

519

Figure D-147.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

520

Figure D-148.Tri-nozzle configuration, Run 193, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.97°, XS = 40.15 in, YS = 0.00 in, CT = 2.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

521

Figure D-148.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

522

Figure D-149.Tri-nozzle configuration, Run 194, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −179.97°, XS = 40.15 in, YS = 0.00 in, CT = 1.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

523

Figure D-149.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

524

Figure D-150.Tri-nozzle configuration, Run 195, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 120.02°, XS = 40.15 in, YS = 0.00 in, CT = 1.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

525

Figure D-150.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

526

Figure D-151.Tri-nozzle configuration, Run 196, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.88°, XS = 40.15 in, YS = 0.00 in, CT = 1.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

527

Figure D-151.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

528

Figure D-152.Tri-nozzle configuration, Run 197, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 1.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

529

Figure D-152.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

530

Figure D-153. Tri-nozzle configuration, Run 198, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

531

Figure D-153.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

532

Figure D-154. Tri-nozzle configuration, Run 199, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.92°, XS = 40.15 in, YS = 0.00 in, CT = 0.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

533

Figure D-154.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

534

Figure D-155. Tri-nozzle configuration, Run 200, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 120.00°, XS = 40.15 in, YS = 0.00 in, CT = 0.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

535

Figure D-155.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

536

Figure D-156. Tri-nozzle configuration, Run 201, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

537

Figure D-156.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

538

Figure D-157. Tri-nozzle configuration, Run 202, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.43.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

539

Figure D-157.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

540

Figure D-158. Tri-nozzle configuration, Run 203, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −179.97°, XS = 40.15 in, YS = 0.00 in, CT = 0.44.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

541

Figure D-158.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

542

Figure D-159. Tri-nozzle configuration, Run 204, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 120.04°, XS = 40.15 in, YS = 0.00 in, CT = 0.43.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

543

Figure D-159.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

544

Figure D-160. Tri-nozzle configuration, Run 205, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.88°, XS = 40.15 in, YS = 0.00 in, CT = 0.44.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

545

Figure D-160.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

546

Figure D-161. Tri-nozzle configuration, Run 206, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.43.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

547

Figure D-161.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

548

Figure D-162. Tri-nozzle configuration, Run 211, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 2.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

549

Figure D-162.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

550

Figure D-163. Tri-nozzle configuration, Run 212, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.96°, XS = 40.15 in, YS = 0.00 in, CT = 2.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

551

Figure D-163.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

552

Figure D-164. Tri-nozzle configuration, Run 213, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.04°, XS = 40.15 in, YS = 0.00 in, CT = 2.87.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

553

Figure D-164.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

554

Figure D-165. Tri-nozzle configuration, Run 214, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 2.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

555

Figure D-165.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

556

Figure D-166. Tri-nozzle configuration, Run 217, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.47.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

557

Figure D-166.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

558

Figure D-167. Tri-nozzle configuration, Run 218, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.88°, XS = 40.15 in, YS = 0.00 in, CT = 0.48.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

559

Figure D-167.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

560

Figure D-168. Tri-nozzle configuration, Run 219, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 120.02°, XS = 40.15 in, YS = 0.00 in, CT = 0.47.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

561

Figure D-168.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

562

Figure D-169. Tri-nozzle configuration, Run 220, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.48.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

563

Figure D-169.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

564

Figure D-170. Tri-nozzle configuration, Run 221, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.24.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

565

Figure D-170.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

566

Figure D-171. Tri-nozzle configuration, Run 222, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 2.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

567

Figure D-171.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

568

Figure D-172. Tri-nozzle configuration, Run 223, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.90°, XS = 40.15 in, YS = 0.00 in, CT = 2.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

569

Figure D-172.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

570

Figure D-173. Tri-nozzle configuration, Run 224, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 120.06°, XS = 40.15 in, YS = 0.00 in, CT = 2.97.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

571

Figure D-173.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

572

Figure D-174. Tri-nozzle configuration, Run 225, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 2.97.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

573

Figure D-174.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

574

Figure D-175. Tri-nozzle configuration, Run 226, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 1.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

575

Figure D-175.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

576

Figure D-176. Tri-nozzle configuration, Run 227, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.04°, XS = 40.15 in, YS = 0.00 in, CT = 1.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

577

Figure D-176.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

578

Figure D-177. Tri-nozzle configuration, Run 228, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.96°, XS = 40.15 in, YS = 0.00 in, CT = 1.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

579

Figure D-177.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

580

Figure D-178. Tri-nozzle configuration, Run 229, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 1.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

581

Figure D-178.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

582

Figure D-179. Tri-nozzle configuration, Run 230, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

583

Figure D-179.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

584

Figure D-180. Tri-nozzle configuration, Run 233, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 59.90°, XS = 40.15 in, YS = 0.00 in, CT = 0.97.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

585

Figure D-180.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

586

Figure D-181. Tri-nozzle configuration, Run 234, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

587

Figure D-181.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

588

Figure D-182. Tri-nozzle configuration, Run 235, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 120.06°, XS = 40.15 in, YS = 0.00 in, CT = 0.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

589

Figure D-182.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

590

Figure D-183. Tri-nozzle configuration, Run 236, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.97.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

591

Figure D-183.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

592

Figure D-184. Tri-nozzle configuration, Run 237, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.48.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

593

Figure D-184.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

594

Figure D-185. Tri-nozzle configuration, Run 238, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.00°, XS = 40.15 in, YS = 0.00 in, CT = 0.47.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

595

Figure D-185.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

596

Figure D-186. Tri-nozzle configuration, Run 239, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.46.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

597

Figure D-186.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

598

Figure D-187. Tri-nozzle configuration, Run 240, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.46.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

599

Figure D-187.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

600

Figure D-188. Tri-nozzle configuration, Run 241, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.23.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

601

Figure D-188.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

602

Figure D-189. Tri-nozzle configuration, Run 242, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 1.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

603

Figure D-189.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

604

Figure D-190. Tri-nozzle configuration, Run 243, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.94°, XS = 40.15 in, YS = 0.00 in, CT = 1.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

605

Figure D-190.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

606

Figure D-191. Tri-nozzle configuration, Run 244, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.06°, XS = 40.15 in, YS = 0.00 in, CT = 1.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

607

Figure D-191.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

608

Figure D-192. Tri-nozzle configuration, Run 245, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −179.99°, XS = 40.15 in, YS = 0.00 in, CT = 1.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

609

Figure D-192.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

610

Figure D-193. Tri-nozzle configuration, Run 247, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 1.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

611

Figure D-193.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

612

Figure D-194. Tri-nozzle configuration, Run 248, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 1.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

613

Figure D-194.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

614

Figure D-195. Tri-nozzle configuration, Run 249, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.90.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

615

Figure D-195.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

616

Figure D-196. Tri-nozzle configuration, Run 250, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.04°, XS = 40.15 in, YS = 0.00 in, CT = 0.90.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

617

Figure D-196.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

618

Figure D-197. Tri-nozzle configuration, Run 251, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.98°, XS = 40.15 in, YS = 0.00 in, CT = 0.89.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

619

Figure D-197.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

620

Figure D-198. Tri-nozzle configuration, Run 252, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.90.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

621

Figure D-198.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

622

Figure D-199. Tri-nozzle configuration, Run 253, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.43.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

623

Figure D-199.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

624

Figure D-200. Tri-nozzle configuration, Run 254, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.43.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

625

Figure D-200.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

626

Figure D-201. Tri-nozzle configuration, Run 255, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.02°, XS = 40.15 in, YS = 0.00 in, CT = 0.42.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

627

Figure D-201.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

628

Figure D-202. Tri-nozzle configuration, Run 256, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.43.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

629

Figure D-202.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

630

Figure D-203. Tri-nozzle configuration, Run 257, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.20.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

631

Figure D-203.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

632

Figure D-204. Tri-nozzle configuration, Run 258, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

633

Figure D-204.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

634

Figure D-205. Tri-nozzle configuration, Run 259, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.90°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

635

Figure D-205.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

636

Figure D-206. Tri-nozzle configuration, Run 260, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.00°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

637

Figure D-206.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

638

Figure D-207. Tri-nozzle configuration, Run 261, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

639

Figure D-207.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

640

Figure D-208. Tri-nozzle configuration, Run 262, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.01°, XS = 40.15 in, YS = 0.00 in, CT = 2.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

641

Figure D-208.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

642

Figure D-209. Tri-nozzle configuration, Run 263, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −179.95°, XS = 40.15 in, YS = 0.00 in, CT = 2.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

643

Figure D-209.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

644

Figure D-210. Tri-nozzle configuration, Run 265, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.91.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

645

Figure D-210.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

646

Figure D-211. Tri-nozzle configuration, Run 266, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.44.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

647

Figure D-211.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

648

Figure D-212. Baseline configuration, Run 271, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

649

Figure D-212.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

650

Figure D-213. Baseline configuration, Run 272, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.92°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

651

Figure D-213.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

652

Figure D-214. Baseline configuration, Run 273, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 120.00°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

653

Figure D-214.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

654

Figure D-215. Baseline configuration, Run 0274, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

655

Figure D-215.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

656

Figure D-216. Baseline configuration, Run 276, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 179.99°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

657

Figure D-216.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

658

Figure D-217. Baseline configuration, Run 277, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.00°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

659

Figure D-217.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

660

Figure D-218. Baseline configuration, Run 278, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.96°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

661

Figure D-218.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

662

Figure D-219. Baseline configuration, Run 279, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = −0.05°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

663

Figure D-219.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

664

Figure D-220. Baseline configuration, Run 280, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −0.05°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

665

Figure D-220.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

666

Figure D-221. Baseline configuration, Run 281, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.92°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

667

Figure D-221.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

668

Figure D-222. Baseline configuration, Run 282, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.02°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

669

Figure D-222.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

670

Figure D-223. Baseline configuration, Run 283, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 179.95°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

671

Figure D-223.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

672

Figure D-224. Quad-nozzle configuration, Run 288, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.03°, XS = 40.17 in, YS = 0.00 in, CT = 1.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

673

Figure D-224.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

674

Figure D-225. Quad-nozzle configuration, Run 289, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 59.98°, XS = 40.17 in, YS = 0.00 in, CT = 1.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

675

Figure D-225.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

676

Figure D-226. Quad-nozzle configuration, Run 290, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 120.04°, XS = 40.17 in, YS = 0.00 in, CT = 1.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

677

Figure D-226.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

678

Figure D-227. Quad-nozzle configuration, Run 291, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.95°, XS = 40.17 in, YS = 0.00 in, CT = 1.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

679

Figure D-227.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

680

Figure D-228. Quad-nozzle configuration, Run 293, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 179.97°, XS = 40.16 in, YS = 0.00 in, CT = 0.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

681

Figure D-228.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

682

Figure D-229. Quad-nozzle configuration, Run 294, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 120.02°, XS = 40.16 in, YS = 0.00 in, CT = 0.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

683

Figure D-229.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

684

Figure D-230. Quad-nozzle configuration, Run 295, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = 59.96°, XS = 40.16 in, YS = 0.00 in, CT = 0.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

685

Figure D-230.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

686

Figure D-231. Quad-nozzle configuration, Run 296, M∞ = 2.4, Re∞ = 1.0x107/ft, 

φ = −0.05°, XS = 40.16 in, YS = 0.00 in, CT = 0.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

687

Figure D-231.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

688

Figure D-232. Quad-nozzle configuration, Run 298, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 0.01°, XS = 40.16 in, YS = 0.00 in, CT = 1.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

689

Figure D-232.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

690

Figure D-233. Quad-nozzle configuration, Run 299, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.92°, XS = 40.16 in, YS = 0.00 in, CT = 1.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

691

Figure D-233.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

692

Figure D-234. Quad-nozzle configuration, Run 300, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.02°, XS = 40.16 in, YS = 0.00 in, CT = 1.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

693

Figure D-234.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

694

Figure D-235. Quad-nozzle configuration, Run 301, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 179.95°, XS = 40.16 in, YS = 0.00 in, CT = 1.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

695

Figure D-235.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

696

Figure D-236. Quad-nozzle configuration, Run 302, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 179.95°, XS = 40.16 in, YS = 0.00 in, CT = 0.91.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

697

Figure D-236.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

698

Figure D-237. Quad-nozzle configuration, Run 303, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 120.08°, XS = 40.16 in, YS = 0.00 in, CT = 0.90.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

699

Figure D-237.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

700

Figure D-238. Quad-nozzle configuration, Run 304, M∞ = 3.5, Re∞ = 1.0x107/ft, 

φ = 59.94°, XS = 40.16 in, YS = 0.00 in, CT = 0.90.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

701

Figure D-238.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

702

Figure D-239. Quad-nozzle configuration, Run 305, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.16 in, YS = 0.00 in, CT = 0.90.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

703

Figure D-239.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

704

Figure D-240. Quad-nozzle configuration, Run 307, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.05°, XS = 40.17 in, YS = 0.00 in, CT = 1.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

705

Figure D-240.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

706

Figure D-241. Quad-nozzle configuration, Run 309, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.88°, XS = 40.17 in, YS = 0.00 in, CT = 1.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

707

Figure D-241.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

708

Figure D-242. Quad-nozzle configuration, Run 310, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.02°, XS = 40.17 in, YS = 0.00 in, CT = 1.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

709

Figure D-242.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

710

Figure D-243. Quad-nozzle configuration, Run 311, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −179.99°, XS = 40.17 in, YS = 0.00 in, CT = 1.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

711

Figure D-243.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

712

Figure D-244. Quad-nozzle configuration, Run 312, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = −179.97°, XS = 40.17 in, YS = 0.00 in, CT = 0.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

713

Figure D-244.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

714

Figure D-245. Quad-nozzle configuration, Run 313, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 120.04°, XS = 40.17 in, YS = 0.00 in, CT = 0.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

715

Figure D-245.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

716

Figure D-246. Quad-nozzle configuration, Run 314, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 59.98°, XS = 40.17 in, YS = 0.00 in, CT = 0.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

717

Figure D-246.Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

718

Figure D-247. Quad-nozzle configuration, Run 315, M∞ = 4.6, Re∞ = 1.5x107/ft, 

φ = 0.05°, XS = 40.17 in, YS = 0.00 in, CT = 0.91.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

719

Figure D-247. Concluded.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

720

APPENDIX E

PRESSURE CONTOUR PLOTS

The pressure data was also used to develop contour maps of the forebody for every test point within a run. 

The contour maps were generated with MatLab based on 2D interpolation/extrapolation of the test data, 

using the griddata function assuming a biharmonic spline fit on a 2D polar grid. Known faulty ports were 

not utilized during the mapping process. Mapping the data in this manner was helpful for doublechecking the list of faulty ports as part of the data analysis process. The contour maps could also be used 

to calculate a rough-order force coefficient for comparison against computational results if needed. The 

following pages, one per run, provide the resulting contour maps for each unique test point (redundant 

points were omitted to reduce the page count). The plots were allowed to auto scale so that the global 

trends could be observed. Direct comparisons between runs can best be accomplished using the line plots 

in the previous appendix.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

721

Figure E-1. Baseline configuration, Run 013, M∞ = 2.4, Re∞ = 1.0x106/ft, φ = 0.03°, 

XS = 25.16 in, YS = 0.04 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

722

Figure E-2. Baseline configuration, Run 014, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.02°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

723

Figure E-3. Baseline configuration, Run 016, M∞ = 2.4, Re∞ = 1.0x106/ft, φ = 0.05°, 

XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

724

Figure E-4. Baseline configuration, Run 017, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.94°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

725

Figure E-5. Baseline configuration, Run 018, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.90°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

726

Figure E-6. Baseline configuration, Run 019, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.93°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

727

Figure E-7. Baseline configuration, Run 020, M∞ = 2.4, Re∞ = 1.0x106/ft, φ = 0.01°, 

XS = 39.93 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

728

Figure E-8. Baseline configuration, Run 021, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.94°, XS = 39.93 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

729

Figure E-9. Baseline configuration, Run 022, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 120.00°, XS = 39.93 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

730

Figure E-10. Baseline configuration, Run 023, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 39.93 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

731

Figure E-11. Baseline configuration, Run 024, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 39.93 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

732

Figure E-12. Baseline configuration, Run 025, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.08°, XS = 39.93 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

733

Figure E-13. Baseline configuration, Run 026, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.03°, XS = 50.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

734

Figure E-14. Baseline configuration, Run 027, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.08°, XS = 50.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

735

Figure E-15. Baseline configuration, Run 028, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 120.06°, XS = 50.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

736

Figure E-16. Baseline configuration, Run 029, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.91°, XS = 50.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

737

Figure E-17. Baseline configuration, Run 030, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.91°, XS = 25.18 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

738

Figure E-18. Baseline configuration, Run 031, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.92°, XS = 25.18 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

739

Figure E-19. Baseline configuration, Run 032, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 25.18 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

740

Figure E-20. Baseline configuration, Run 033, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 25.18 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

741

Figure E-21. Baseline configuration, Run 034, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 25.18 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

742

Figure E-22. Baseline configuration, Run 035, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.08°, XS = 25.18 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

743

Figure E-23. Baseline configuration, Run 036, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.90°, XS = 25.18 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

744

Figure E-24. Baseline configuration, Run 037, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 25.18 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

745

Figure E-25. Baseline configuration, Run 038, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.19 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

746

Figure E-26. Baseline configuration, Run 039, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.90°, XS = 40.19 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

747

Figure E-27. Baseline configuration, Run 040, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.19 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

748

Figure E-28. Baseline configuration, Run 041, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 40.19 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

749

Figure E-29. Baseline configuration, Run 042, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.19 in, YS = −8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

750

Figure E-30. Baseline configuration, Run 043, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.92°, XS = 40.19 in, YS = −8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

751

Figure E-31. Baseline configuration, Run 044, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.90°, XS = 40.19 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

752

Figure E-32. Baseline configuration, Run 045, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.19 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

753

Figure E-33. Baseline configuration, Run 046, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 50.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

754

Figure E-34. Baseline configuration, Run 047, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.92°, XS = 50.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

755

Figure E-35. Baseline configuration, Run 048, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 50.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

756

Figure E-36. Baseline configuration, Run 049, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 50.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

757

Figure E-37. Baseline configuration, Run 050, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.02°, XS = 50.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

758

Figure E-38. Baseline configuration, Run 051, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.94°, XS = 50.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

759

Figure E-39. Baseline configuration, Run 052, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 50.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

760

Figure E-40. Baseline configuration, Run 053, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 39.93 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

761

Figure E-41. Baseline configuration, Run 054, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.06°, XS = 40.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

762

Figure E-42. Baseline configuration, Run 055, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

763

Figure E-43. Baseline configuration, Run 056, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.07°, XS = 40.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

764

Figure E-44. Baseline configuration, Run 057, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.07°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

765

Figure E-45. Baseline configuration, Run 058, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.04°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

766

Figure E-46. Baseline configuration, Run 059, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.06°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

767

Figure E-47. Baseline configuration, Run 060, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 25.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

768

Figure E-48. Baseline configuration, Run 065, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 25.16 in, YS = −8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

769

Figure E-49. Baseline configuration, Run 067, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.06°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

770

Figure E-50. Baseline configuration, Run 068, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.96°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

771

Figure E-51. Baseline configuration, Run 069, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

772

Figure E-52. Baseline configuration, Run 070, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

773

Figure E-53. Baseline configuration, Run 073, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.92°, XS = 40.18 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

774

Figure E-54. Baseline configuration, Run 074, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.02°, XS = 40.18 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

775

Figure E-55. Baseline configuration, Run 075, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.03°, XS = 40.18 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

776

Figure E-56. Baseline configuration, Run 076, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.03°, XS = 40.18 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

777

Figure E-57. Baseline configuration, Run 077, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.16 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

778

Figure E-58. Baseline configuration, Run 078, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.92°, XS = 40.16 in, YS = 7.95 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

779

Figure E-59. Baseline configuration, Run 079, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −179.99°, XS = 40.16 in, YS = 7.95 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

780

Figure E-60. Baseline configuration, Run 080, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −179.99°, XS = 50.15 in, YS = 7.95 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

781

Figure E-61. Baseline configuration, Run 081, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.92°, XS = 50.15 in, YS = 7.95 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

782

Figure E-62. Baseline configuration, Run 082, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.00°, XS = 50.15 in, YS = 7.95 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

783

Figure E-63. Baseline configuration, Run 083, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 50.15 in, YS = 7.95 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

784

Figure E-64. Baseline configuration, Run 086, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 0.01°, XS = 25.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

785

Figure E-65. Baseline configuration, Run 087, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 60.04°, XS = 25.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

786

Figure E-66. Baseline configuration, Run 088, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 119.90°, XS = 25.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

787

Figure E-67. Baseline configuration, Run 089, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 179.91°, XS = 25.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

788

Figure E-68. Baseline configuration, Run 090, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

789

Figure E-69. Baseline configuration, Run 091, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 60.00°, XS = 40.18 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

790

Figure E-70. Baseline configuration, Run 092, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 119.92°, XS = 40.18 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

791

Figure E-71. Baseline configuration, Run 093, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 179.91°, XS = 40.18 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

792

Figure E-72. Baseline configuration, Run 094, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 179.91°, XS = 50.14 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

793

Figure E-73. Baseline configuration, Run 095, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 119.90°, XS = 50.14 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

794

Figure E-74. Baseline configuration, Run 096, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 59.96°, XS = 50.14 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

795

 

Figure E-75. Baseline configuration, Run 097, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = −0.07°, XS = 50.14 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

796

Figure E-76. Baseline configuration, Run 098, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = −0.07°, XS = 50.14 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

797

Figure E-77. Baseline configuration, Run 099, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 59.92°, XS = 50.14 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

798

Figure E-78. Baseline configuration, Run 100, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 120.00°, XS = 50.14 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

799

Figure E-79. Baseline configuration, Run 101, M∞ = 4.6, Re∞ = 1.1x106/ft, 

φ = 179.97°, XS = 50.14 in, YS = 7.99 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

800

Figure E-80. Baseline configuration, Run 104, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.03°, XS = 25.19 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

801

Figure E-81. Baseline configuration, Run 105, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 60.00°, XS = 25.19 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

802

Figure E-82. Baseline configuration, Run 106, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.96°, XS = 25.19 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

803

Figure E-83. Baseline configuration, Run 107, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.93°, XS = 25.19 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

804

Figure E-84. Baseline configuration, Run 108, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.93°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

805

Figure E-85. Baseline configuration, Run 109, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.92°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

806

Figure E-86. Baseline configuration, Run 110, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 59.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

807

Figure E-87. Baseline configuration, Run 111, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.01°, XS = 40.09 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

808

Figure E-88. Baseline configuration, Run 112, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.01°, XS = 50.19 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

809

Figure E-89. Baseline configuration, Run 113, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 60.02°, XS = 50.19 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

810

Figure E-90. Baseline configuration, Run 114, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 120.04°, XS = 50.19 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

811

Figure E-91. Baseline configuration, Run 115, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.97°, XS = 50.19 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

812

Figure E-92. Baseline configuration, Run 116, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.97°, XS = 50.19 in, YS = 8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

813

Figure E-93. Baseline configuration, Run 117, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.92°, XS = 50.19 in, YS = 8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

814

Figure E-94. Baseline configuration, Run 118, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 59.96°, XS = 50.19 in, YS = 8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

815

Figure E-95. Baseline configuration, Run 119, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.03°, XS = 50.19 in, YS = 8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

816

Figure E-96. Baseline configuration, Run 120, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.03°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

817

Figure E-97. Baseline configuration, Run 121, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 60.06°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

818

Figure E-98. Baseline configuration, Run 122, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 120.00°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

819

Figure E-99. Baseline configuration, Run 123, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.91°, XS = 25.16 in, YS = –8.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

820

Figure E-100. Center nozzle configuration, Run 136, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = –0.01°, XS = 40.16 in, YS = 0.00 in, CT = 4.03.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

821

Figure E-101. Center nozzle configuration, Run 137, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 2.99.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

822

Figure E-102. Center nozzle configuration, Run 138, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 3.01.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

823

Figure E-103. Center nozzle configuration, Run 139, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 0.97.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

824

Figure E-104. Center nozzle configuration, Run 140, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = –0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.97.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

825

Figure E-105. Center nozzle configuration, Run 141, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 1.98.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

826

Figure E-106. Center nozzle configuration, Run 142, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.91°, XS = 40.15 in, YS = 0.00 in, CT = 1.99.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

827

Figure E-107. Center nozzle configuration, Run 143, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.91°, XS = 40.15 in, YS = 0.00 in, CT = 0.46.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

828

Figure E-108. Center nozzle configuration, Run 144, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.47.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

829

Figure E-109. Center nozzle configuration, Run 145, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.23.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

830

Figure E-110. Center nozzle configuration, Run 146, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.23.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

831

Figure E-111. Center nozzle configuration, Run 147, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −180.00°, XS = 40.15 in, YS = 0.00 in, CT = 0.19.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

832

Figure E-112. Center nozzle configuration, Run 148, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

833

Figure E-113. Center nozzle configuration, Run 149, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

834

Figure E-114. Center nozzle configuration, Run 150, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.17 in, YS = 0.00 in, CT = 2.99.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

835

Figure E-115. Center nozzle configuration, Run 151, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −179.97°, XS = 40.17 in, YS = 0.00 in, CT = 3.01.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

836

Figure E-116. Center nozzle configuration, Run 152, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −179.97°, XS = 40.17 in, YS = 0.00 in, CT = 1.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

837

Figure E-117. Center nozzle configuration, Run 153, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.09°, XS = 40.17 in, YS = 0.00 in, CT = 1.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

838

Figure E-118. Center nozzle configuration, Run 154, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.09°, XS = 40.17 in, YS = 0.00 in, CT = 0.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

839

Figure E-119. Center nozzle configuration, Run 155, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.91°, XS = 40.17 in, YS = 0.00 in, CT = 0.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

840

Figure E-120. Center nozzle configuration, Run 156, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.93°, XS = 40.17 in, YS = 0.00 in, CT = 0.45.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

841

Figure E-121. Center nozzle configuration, Run 157, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.07°, XS = 40.17 in, YS = 0.00 in, CT = 0.45.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

842

Figure E-122. Center nozzle configuration, Run 159, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.17 in, YS = 0.00 in, CT = 0.21.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

843

Figure E-123. Center nozzle configuration, Run 160, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.93°, XS = 40.17 in, YS = 0.00 in, CT = 0.21.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

844

Figure E-124. Center nozzle configuration, Run 161, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.93°, XS = 40.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

845

Figure E-125. Center nozzle configuration, Run 162, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.03°, XS = 40.17 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

846

Figure E-126. Center nozzle configuration, Run 163, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.03°, XS = 40.17 in, YS = 0.00 in, CT = 2.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

847

Figure E-127. Center nozzle configuration, Run 164, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 1479.91°, XS = 40.17 in, YS = 0.00 in, CT = 2.91.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

848

Figure E-128. Center nozzle configuration, Run 165, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.93°, XS = 40.15 in, YS = 0.00 in, CT = 1.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

849

Figure E-129. Center nozzle configuration, Run 166, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.03°, XS = 40.15 in, YS = 0.00 in, CT = 1.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

850

Figure E-130. Center nozzle configuration, Run 167, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

851

Figure E-131. Center nozzle configuration, Run 168, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

852

Figure E-132. Center nozzle configuration, Run 169, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.45.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

853

Figure E-133. Center nozzle configuration, Run 170, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.46.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

854

Figure E-134. Center nozzle configuration, Run 171, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.22.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

855

Figure E-135. Center nozzle configuration, Run 172, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.91°, XS = 40.15 in, YS = 0.00 in, CT = 0.22.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

856

Figure E-136. Center nozzle configuration, Run 173, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.91°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

857

Figure E-137. Center nozzle configuration, Run 174, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.07°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

858

Figure E-138. Tri-nozzle configuration, Run 179, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.09°, XS = 40.15 in, YS = 0.00 in, CT = 2.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

859

Figure E-139. Tri-nozzle configuration, Run 180, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

860

Figure E-140. Tri-nozzle configuration, Run 181, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

861

Figure E-141. Tri-nozzle configuration, Run 182, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.96°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

862

Figure E-142. Tri-nozzle configuration, Run 183, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.04°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

863

Figure E-143. Tri-nozzle configuration, Run 184, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

864

Figure E-144. Tri-nozzle configuration, Run 185, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 59.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

865

Figure E-145. Tri-nozzle configuration, Run 186, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

866

Figure E-146. Tri-nozzle configuration, Run 187, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

867

Figure E-147. Tri-nozzle configuration, Run 190, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 2.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

868

Figure E-148. Tri-nozzle configuration, Run 191, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 58.37°, XS = 40.15 in, YS = 0.00 in, CT = 2.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

869

Figure E-149. Tri-nozzle configuration, Run 192, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.94°, XS = 40.15 in, YS = 0.00 in, CT = 2.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

870

Figure E-150. Tri-nozzle configuration, Run 193, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.97°, XS = 40.15 in, YS = 0.00 in, CT = 2.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

871

Figure E-151. Tri-nozzle configuration, Run 194, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.97°, XS = 40.15 in, YS = 0.00 in, CT = 1.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

872

Figure E-152. Tri-nozzle configuration, Run 195, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.96°, XS = 40.15 in, YS = 0.00 in, CT = 1.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

873

Figure E-153. Tri-nozzle configuration, Run 196, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.94°, XS = 40.15 in, YS = 0.00 in, CT = 1.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

874

Figure E-154. Tri-nozzle configuration, Run 197, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 1.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

875

Figure E-155. Tri-nozzle configuration, Run 198, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

876

Figure E-156. Tri-nozzle configuration, Run 199, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.15 in, YS = 0.00 in, CT = 0.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

877

Figure E-157. Tri-nozzle configuration, Run 200, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

878

Figure E-158. Tri-nozzle configuration, Run 201, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

879

Figure E-159. Tri-nozzle configuration, Run 202, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.43.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

880

Figure E-160. Tri-nozzle configuration, Run 203, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.97°, XS = 40.15 in, YS = 0.00 in, CT = 0.44.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

881

Figure E-161. Tri-nozzle configuration, Run 204, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.98°, XS = 40.15 in, YS = 0.00 in, CT = 0.44.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

882

Figure E-162. Tri-nozzle configuration, Run 205, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.43.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

883

Figure E-163. Tri-nozzle configuration, Run 206, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.43.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

884

Figure E-164. Tri-nozzle configuration, Run 211, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 2.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

885

Figure E-165. Tri-nozzle configuration, Run 212, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 60.02°, XS = 40.15 in, YS = 0.00 in, CT = 2.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

886

Figure E-166. Tri-nozzle configuration, Run 213, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.98°, XS = 40.15 in, YS = 0.00 in, CT = 2.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

887

Figure E-167. Tri-nozzle configuration, Run 214, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 2.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

888

Figure E-168. Tri-nozzle configuration, Run 217, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.48.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

889

Figure E-169. Tri-nozzle configuration, Run 218, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.48.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

890

Figure E-170. Tri-nozzle configuration, Run 219, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.96°, XS = 40.15 in, YS = 0.00 in, CT = 0.48.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

891

Figure E-171. Tri-nozzle configuration, Run 220, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.48.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

892

Figure E-172. Tri-nozzle configuration, Run 221, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 0.23.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

893

Figure E-173. Tri-nozzle configuration, Run 222, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.01°, XS = 40.15 in, YS = 0.00 in, CT = 2.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

894

Figure E-174. Tri-nozzle configuration, Run 223, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 59.96°, XS = 40.15 in, YS = 0.00 in, CT = 2.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

895

Figure E-175. Tri-nozzle configuration, Run 224, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.00°, XS = 40.15 in, YS = 0.00 in, CT = 3.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

896

Figure E-176. Tri-nozzle configuration, Run 225, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 2.98.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

897

Figure E-177. Tri-nozzle configuration, Run 226, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.15 in, YS = 0.00 in, CT = 1.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

898

Figure E-178. Tri-nozzle configuration, Run 227, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.98°, XS = 40.15 in, YS = 0.00 in, CT = 1.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

899

Figure E-179. Tri-nozzle configuration, Run 228, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.02°, XS = 40.15 in, YS = 0.00 in, CT = 1.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

900

Figure E-180. Tri-nozzle configuration, Run 229, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 1.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

901

Figure E-181. Tri-nozzle configuration, Run 230, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.97.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

902

Figure E-182. Tri-nozzle configuration, Run 233, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 59.96°, XS = 40.15 in, YS = 0.00 in, CT = 0.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

903

Figure E-183. Tri-nozzle configuration, Run 234, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.97.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

904

Figure E-184. Tri-nozzle configuration, Run 235, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.00°, XS = 40.15 in, YS = 0.00 in, CT = 0.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

905

Figure E-185. Tri-nozzle configuration, Run 236, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

906

Figure E-186. Tri-nozzle configuration, Run 237, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.47.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

907

Figure E-187. Tri-nozzle configuration, Run 238, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.47.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

908

Figure E-188. Tri-nozzle configuration, Run 239, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.00°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

909

Figure E-189. Tri-nozzle configuration, Run 240, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.46.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

910

Figure E-190. Tri-nozzle configuration, Run 241, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.22.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

911

Figure E-191. Tri-nozzle configuration, Run 242, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 1.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

912

Figure E-192. Tri-nozzle configuration, Run 243, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 60.00°, XS = 40.15 in, YS = 0.00 in, CT = 1.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

913

Figure E-193. Tri-nozzle configuration, Run 244, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 120.00°, XS = 40.15 in, YS = 0.00 in, CT = 1.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

914

Figure E-194. Tri-nozzle configuration, Run 245, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −179.99°, XS = 40.15 in, YS = 0.00 in, CT = 1.97.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

915

Figure E-195. Tri-nozzle configuration, Run 247, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 1.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

916

Figure E-196. Tri-nozzle configuration, Run 248, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 1.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

917

Figure E-197. Tri-nozzle configuration, Run 249, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 0.90.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

918

Figure E-198. Tri-nozzle configuration, Run 250, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.96°, XS = 40.15 in, YS = 0.00 in, CT = 0.90.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

919

Figure E-199. Tri-nozzle configuration, Run 251, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 60.04°, XS = 40.15 in, YS = 0.00 in, CT = 0.90.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

920

Figure E-200. Tri-nozzle configuration, Run 252, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.90.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

921

Figure E-201. Tri-nozzle configuration, Run 253, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.42.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

922

Figure E-202. Tri-nozzle configuration, Run 254, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 60.00°, XS = 40.15 in, YS = 0.00 in, CT = 0.42.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

923

Figure E-203. Tri-nozzle configuration, Run 255, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.96°, XS = 40.15 in, YS = 0.00 in, CT = 0.42.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

924

Figure E-204. Tri-nozzle configuration, Run 256, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.43.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

925

Figure E-205. Tri-nozzle configuration, Run 257, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.20.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

926

Figure E-206. Tri-nozzle configuration, Run 258, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.03°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

927

Figure E-207. Tri-nozzle configuration, Run 259, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 59.96°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

928

Figure E-208. Tri-nozzle configuration, Run 260, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.94°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

929

Figure E-209. Tri-nozzle configuration, Run 261, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.95°, XS = 40.15 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

930

Figure E-210. Tri-nozzle configuration, Run 262, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.01°, XS = 40.15 in, YS = 0.00 in, CT = 2.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

931

Figure E-211. Tri-nozzle configuration, Run 263, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −179.99°, XS = 40.15 in, YS = 0.00 in, CT = 2.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

932

Figure E-212. Tri-nozzle configuration, Run 264, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.99°, XS = 40.15 in, YS = 0.00 in, CT = 5.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

933

Figure E-213. Tri-nozzle configuration, Run 265, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.91.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

934

Figure E-214. Tri-nozzle configuration, Run 266, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 0.45.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

935

Figure E-215. Tri-nozzle configuration, Run 267, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.15 in, YS = 0.00 in, CT = 4.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

936

Figure E-216. Baseline configuration, Run 271, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

937

Figure E-217. Baseline configuration, Run 272, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

938

Figure E-218. Baseline configuration, Run 273, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.94°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

939

Figure E-219. Baseline configuration, Run 0274, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

940

Figure E-220. Baseline configuration, Run 276, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.99°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

941

Figure E-221. Baseline configuration, Run 277, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.94°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

942

Figure E-222. Baseline configuration, Run 278, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.00°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

943

Figure E-223. Baseline configuration, Run 279, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

944

Figure E-224. Baseline configuration, Run 280, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −0.05°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

945

Figure E-225. Baseline configuration, Run 281, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 59.98°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

946

Figure E-226. Baseline configuration, Run 282, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.96°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

947

Figure E-227. Baseline configuration, Run 283, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 179.97°, XS = 40.16 in, YS = 0.00 in, CT = 0.00.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

948

Figure E-228. Quad-nozzle configuration, Run 288, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.17 in, YS = 0.00 in, CT = 1.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

949

Figure E-229. Quad-nozzle configuration, Run 289, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.17 in, YS = 0.00 in, CT = 1.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

950

Figure E-230. Quad-nozzle configuration, Run 290, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.98°, XS = 40.17 in, YS = 0.00 in, CT = 1.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

951

Figure E-231. Quad-nozzle configuration, Run 291, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −179.95°, XS = 40.17 in, YS = 0.00 in, CT = 1.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

952

Figure E-232. Quad-nozzle configuration, Run 292, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 149.95°, XS = 40.16 in, YS = 0.00 in, CT = 1.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

953

Figure E-233. Quad-nozzle configuration, Run 293, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 179.97°, XS = 40.16 in, YS = 0.00 in, CT = 0.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

954

Figure E-234. Quad-nozzle configuration, Run 294, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 119.96°, XS = 40.16 in, YS = 0.00 in, CT = 0.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

955

Figure E-235. Quad-nozzle configuration, Run 295, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 60.02°, XS = 40.16 in, YS = 0.00 in, CT = 0.94.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

956

Figure E-236. Quad-nozzle configuration, Run 296, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = −0.05°, XS = 40.16 in, YS = 0.00 in, CT = 0.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

957

Figure E-237. Quad-nozzle configuration, Run 297, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 30.03°, XS = 40.15 in, YS = 0.00 in, CT = 2.95.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

958

Figure E-238. Quad-nozzle configuration, Run 298, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 40.16 in, YS = 0.00 in, CT = 1.91.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

959

Figure E-239. Quad-nozzle configuration, Run 299, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 59.98°, XS = 40.16 in, YS = 0.00 in, CT = 1.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

960

Figure E-240. Quad-nozzle configuration, Run 300, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 119.96°, XS = 40.16 in, YS = 0.00 in, CT = 1.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

961

Figure E-241. Quad-nozzle configuration, Run 301, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.16 in, YS = 0.00 in, CT = 1.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

962

Figure E-242. Quad-nozzle configuration, Run 302, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 179.95°, XS = 40.16 in, YS = 0.00 in, CT = 0.90.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

963

Figure E-243. Quad-nozzle configuration, Run 303, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 120.02°, XS = 40.16 in, YS = 0.00 in, CT = 0.89.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

964

Figure E-244. Quad-nozzle configuration, Run 304, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 60.00°, XS = 40.16 in, YS = 0.00 in, CT = 0.90.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

965

Figure E-245. Quad-nozzle configuration, Run 305, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = −0.03°, XS = 40.16 in, YS = 0.00 in, CT = 0.90.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

966

Figure E-246. Quad-nozzle configuration, Run 306, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 29.99°, XS = 40.17 in, YS = 0.00 in, CT = 2.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

967

Figure E-247. Quad-nozzle configuration, Run 307, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.05°, XS = 40.17 in, YS = 0.00 in, CT = 1.93.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

968

Figure E-248. Quad-nozzle configuration, Run 309, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 59.94°, XS = 40.17 in, YS = 0.00 in, CT = 1.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

969

Figure E-249. Quad-nozzle configuration, Run 310, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 119.96°, XS = 40.17 in, YS = 0.00 in, CT = 1.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

970

Figure E-250. Quad-nozzle configuration, Run 311, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −179.97°, XS = 40.17 in, YS = 0.00 in, CT = 1.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

971

Figure E-251. Quad-nozzle configuration, Run 312, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = −179.97°, XS = 40.17 in, YS = 0.00 in, CT = 0.91.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

972

Figure E-252. Quad-nozzle configuration, Run 313, M∞ = 4.6, Re∞ = 1.5x106/ft,

φ = 119.98°, XS = 40.17 in, YS = 0.00 in, CT = 0.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

973

Figure E-253. Quad-nozzle configuration, Run 314, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 60.04°, XS = 40.17 in, YS = 0.00 in, CT = 0.91.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

974

Figure E-254. Quad-nozzle configuration, Run 315, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.05°, XS = 40.17 in, YS = 0.00 in, CT = 0.92.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

975

Figure E-255. Center nozzle configuration, Run 319, M∞ = 2.4, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 37.47 in, YS = 0.00 in, CT = 0.45.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

976

Figure E-256. Center nozzle configuration, Run 320, M∞ = 3.5, Re∞ = 1.0x106/ft, 

φ = 0.01°, XS = 43.35 in, YS = 0.00 in, CT = 1.96.
Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind Tunnel Test Section 2

977

Figure E-257. Center nozzle configuration, Run 321, M∞ = 4.6, Re∞ = 1.5x106/ft, 

φ = 0.01°, XS = 42.98 in, YS = 0.00 in, CT = 1.96.
REPORT DOCUMENTATION PAGE Form Approved

OMB No. 0704-0188

2. REPORT TYPE 

Technical Publication

 4. TITLE AND SUBTITLE

Supersonic Retropropulsion Test 1853 in NASA LaRC Unitary Plan Wind 

Tunnel Test Section 2 

5a. CONTRACT NUMBER

 6. AUTHOR(S)

Berry, Scott A.; Rhode, Matthew N.

 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)

NASA Langley Research Center

Hampton, VA 23681-2199

 9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)

National Aeronautics and Space Administration

Washington, DC 20546-0001

 8. PERFORMING ORGANIZATION

 REPORT NUMBER

L-20392

10. SPONSOR/MONITOR'S ACRONYM(S)

NASA

13. SUPPLEMENTARY NOTES

12. DISTRIBUTION/AVAILABILITY STATEMENT

Unclassified - Unlimited

Subject Category 34

Availability: NASA CASI (443) 757-5802

19a. NAME OF RESPONSIBLE PERSON

STI Help Desk (email: help@sti.nasa.gov)

14. ABSTRACT

A supersonic retropropulsion experiment was conducted in the Langley Research Center Unitary Plan Wind Tunnel Test Section 2 at Mach numbers of 2.4, 

3.5, and 4.6. Intended as a code validation effort, this study used pretest computations to size and refine the model such that tunnel blockage and internal flow 

separations were minimized. A 5-in diameter 70 degree sphere-cone forebody, which can accommodate up to four 4:1 area ratio nozzles, followed by a 9.55 

inches long cylindrical aft body was selected for this test after computational maturation. The primary measurements for this experiment were high 

spatial-density surface pressures. In addition, high speed schlieren video and internal pressures and temperatures were acquired. The test included parametric 

variations in the number of nozzles utilized, thrust coefficients (roughly 0 to 4), and angles of attack (–8 to 20 degrees). The run matrix was developed to also 

allow quantification of various sources of experimental uncertainty, such as random errors due to run-to-run variations and systematic errors due to flowfield or 

model misalignments. To accommodate the uncertainty assessment, many runs and replicates were conducted with the model at various locations within the 

tunnel and with model roll angles of 0, 60, 120, and 180 degrees. This test report provides operational details of the experiment, contains a review of trends, 

and provides all schlieren and pressure results within appendices. 

15. SUBJECT TERMS

Decelerators; Experimental; Retropropulsion; Supersonic

18. NUMBER

 OF 

 PAGES

1016

19b. TELEPHONE NUMBER (Include area code)

(443) 757-5802

a. REPORT

U

c. THIS PAGE

U

b. ABSTRACT

U

17. LIMITATION OF 

 ABSTRACT

UU

Prescribed by ANSI Std. Z39.18

Standard Form 298 (Rev. 8-98)

3. DATES COVERED (From - To)

5b. GRANT NUMBER

5c. PROGRAM ELEMENT NUMBER

5d. PROJECT NUMBER

5e. TASK NUMBER

5f. WORK UNIT NUMBER

902152.01.07.01

11. SPONSOR/MONITOR'S REPORT

 NUMBER(S)

NASA/TP-2014-218256

16. SECURITY CLASSIFICATION OF:

The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, 

gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this 

collection of information, including suggestions for reducing this burden, to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and 

Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person 

shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number.

PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS.

1. REPORT DATE (DD-MM-YYYY)

01- 04 - 2014