National Aeronautics and Space Administration 

Wind Tunnel 

Testing Guide 

Aerosciences Evaluation and Test Capabilities Portfolio 

The Right Facility at the Right Time 

Comprehensive Capabilities 

Nowhere in the world are there as many aerospace ground testing facilities as exist at NASA. 

Offering the most complete suite of facilities; all specifically built to collect, analyze and 

interpret test data. 

Aerosciences Evaluation and Test Capabilities (AETC) is setting the strategic direction for 

NASA’s versatile and comprehensive portfolio of ground test aeroscience research 

capabilities including subsonic, transonic, supersonic and hypersonic wind tunnels and 

propulsion test facilities. 

AETC provides critical evaluation and support for NASA’s Aeronautics and Space Missions 

with world class wind tunnel testing including the development of new test technologies and 

facility capabilities. The state-of-the art testing support is a crucial component in the 

advancement of innovative technologies that will take NASA into the future, expand the 

human presence into space, further the understanding of our solar system, provide benefits to 

humanity, and national and international collaboration. 

A One-Stop Setting 

All types of vehicles, from subsonic through hypersonic, have been evaluated at NASA. 

Our unique infrastructure is complemented by unmatched computational capabilities, 

including state-of-the art tools, access to world-renowned specialists and extensive 

code validation. 

In addition, test article fabrication capabilities, advanced instrumentation, cutting-edge 

test techniques, a diverse, highly skilled and experienced workforce, and excellent data 

support are all available and we continually invest to maintain, upgrade, and modernize 

our facilities to keep pace with customer requirements. 

Delivering Solutions to Complex Challenges 

We have a critical mass of subject-matter experts with internationally recognized core 

competencies in aero-sciences, acoustics, structures, and materials to identify and deliver 

solutions to your complex aerospace systems challenges. 

Doing Business with Us 

Our extensive aerospace expertise and unique ground testing 

capabilities will prove invaluable to your enterprise. 

We have the most comprehensive ground testing capabilities in the world, 

and we want to share with you the benefits of our decades of 

accomplishments. We offer what others can’t. 

Infrastructure. Know-how. Experience. 

And most importantly: Success. 

The solution to your aerospace challenges starts by contacting: 

www.nasa.gov/aeroresearch/programs/AAVP/AETC

National Aeronautics and Space Administration Dr. Ron Colantonio, Manager 

NASA Headquarters Chris Mouring, Deputy Manager 300 E. Street SW, Suite 5R30 

Washington, DC 20546 Steve Helland, Associate Manager 

www.nasa.gov/aeroresearch/programs/AAVP/AETC 

www.nasa.gov 

NP-2018-11-127-LaRC 
 

 

Facility Capabilities at a Glance Sample Test Capabilities* Specialized Test Techniques* 

Facility Speed Site Reynolds Number Test Section Size Total Pressure Total Temperature Test Gas Type Sample Test Capabilities 

SUBSONIC SPEED RANGE 

14-by 22 Foot Subsonic Tunnel (14 x 22) Mach 0 to 0.3 (348 ft/s) NASA LaRC 0 to 2.2 x 106 per ft 14.5’ H x 21.75’ W x 50’ L Atmospheric Ambient Air Closed Circuit, open or 

closed test section 

AC, FF, FO, GE, SC, HA, P, JET, R, SS, PAAI 

20-Foot Vertical Spin Tunnel (VST) 0 to 90 ft/s NASA LaRC 0 to 0.55 x 106 per ft 25’ H x 20’ W Atmospheric Ambient Air Closed-throat, annular 

return 

FF, FO, SC, HA 

9-by 15 Foot Low Speed Wind Tunnel (LSWT) Mach 0 to 0.21 NASA Glenn 0 to 1.4 x 106 per ft 9‘ H x 15’ Wx 33‘ L 0 to 72 psf Ambient to 550°R Air Atmospheric PSP, Aero, UHB, PIV, PAAI 

Icing Research Tunnel (IRT) 

TRANSONIC SPEED REGIME 

Mach 0.05 to 0.50 NASA Glenn 0 to 3.6 x 106 per ft 6’ H x 9‘ W x 20’ L 0 to 230 psf Ambient to -35° Air Closed Return - 

Atmospheric 

In-flight icing tests and simulations 

Transonic Dynamics Tunnel (TDT) Air Mode: 

Heavy Gas Mode: 

Mach 0 to 1.2 

Mach 0 to 1.2 

NASA LaRC 0.01 to 3.0 x 106 per ft 

0.1 to 9.6 x 106 per ft

16’ H x 16’ W 0.5 psia to atmospheric 70° to 130° Air 

R-134a 

Closed Circuit AE, FO, SC, R, SS 

National Transonic Facility (NTF) Air Mode: 

Cryogenic Mode: 

Mach 0.1 to 1.05 

Mach 0.1 to 1.20 

NASA LaRC 1 to 23 x 106 per ft 

4 to 140 x 106 per ft 

8.2’ H x 8.2’ W x 25’ L 14.7 to 120 psia +70° to +130° 

-250° to +130° 

Air 

Nitrogen 

Closed Circuit PSP, TSP, Model Deformation Systems, 

SC, HA, JET, PT, SS 

11-by 11 Foot Unitary Plan Transonic Wind Tunnel 

SUPERSONIC SPEED REGIME 

Mach 0.2 to 1.45 NASA Ames 0.3 to 9.6 x 106 per ft 11‘ H x 11’W x 22‘ L 432-4608 psfa 110 ± 20°F Air Closed Return PSP, PIV, OF, IR, SI 

4-Foot Supersonic Unitary Plan Wind Tunnel (UPWT) Test Section 1: 

Test Section 2: 

Mach 1.5 to 2.9 

Mach 2.3 to 4.6 

NASA LaRC 0.5 to 11.4 x 106 per ft 

0.5 to 8.4 x 106 per ft 

4’ H x 4’ W x 7’ L 0 to 10 atmospheres 100° to 300° Dry Air Closed Circuit AT, FO, SC, HA, JET, PT, SS 

9-by 7 Foot Unitary Plan Wind Tunnel Mach 1.55 to 2.55 NASA Ames 0.9 to 5.6 x 106 per ft 9’ H x 7’ W x 18’ L 634-3888 psfa 110 ± 20°F Air Closed Return IR, PSP, OF, ADST 

10-by 10 Foot Foot Wind Tunnel Mach 0 to 0.36, 2.0 to 3.5 NASA Glenn 0.12 to 3.4 x 106 per ft 10’ H x 10’ W x 40’ L 20 to 720 psf 520 to 1140°R Air Open or Closed Circuit PSP, SS, PIV, PT 

8-by 6 Foot Supersonic Wind Tunnel 0 to 0.1, 0.25 to 2.0 NASA Glenn 1.5 to 5.5 x 106 per ft 8’ W x 6’ H x 23.5’ L 100 to 1340 psf 520 to 720°R Air Open or Closed Circuit, 

Atmospheric 

PSP, SS, P 

Propulsion Systems Lab 

HYPERSONIC SPEED REGIME 

Langley Aerothermal Dynamics Laboratory (LAL)

0 to 3.5, 0 to 6.0 w/ topping 

heater 

NASA Glenn n/a 12’ x 12’ x 39’ 150 psig 850°F Air Non Vitiated Altitude icing simulations 

 20-Inch Mach 6 Air Tunnel Mach 6 NASA LaRC 0.5 to 8.0 x 106 per ft 20” H x 20.5” W 30 to 475 psia 760° to 940°R Dry Air Blow Down AT, JET, TSP, PSP, High AOA, IR, High 

Speed Schlieren, BOS, PLIF, Oil Flow 

 15-Inch Mach 6 High Temperature Tunnel Mach 6 NASA LaRC 0.5 to 6.0 x 106 per ft 14.6” diameter open jet 50 to 450 psia 870°-1260° R Dry Air Blow Down AT, JET, TSP, PSP, High AOA, IR, High 

Speed Schlieren, BOS, PLIF, Oil Flow 

 31-Inch Mach 10 Air Tunnel Mach 10 NASA LaRC 0.5 to 2.2 x 106 per ft 31” H x 31” W 150 to 1450 psia 1850°R Dry Air Blow Down AT, JET, TSP, PSP, High AOA, IR, High 

Speed Schlieren, BOS, PLIF, Oil Flow 

8-Foot High Temperature Tunnel (8-ft HTT) Mach 3, 5 NASA LaRC 0.44 to 5.09 x 106 per ft 54.5” diameter Mach 3, 5 50 to 4000 psia 850° to 4000° Air Blow Down AT, P 

Mach 4, 5, and 7 96” diameter Mach 4, 5, & 7 

IR Infrared Flow 

Visual 

AFL Airfoil Testing to 

Ground Wind Loads 

FO Forced Oscillation 

Testing 

PAAI Propulsion Airframe 

Aeroacoustic 

Integration 

RT Rotorcraft 

Testing 

The following optical measurement techniques are in 

routine use at AETC facilities. 

IR Thermography 

Real-time measurement of surface temperature suitable for 

measuring heat flux, flow separation, and boundary layer 

transition location. Adaptive contrast enhancement algorithms 

are used to aid visualization of subtle temperature features. 

AC Acoustic AE Aeroelastic Pressure/Temperature-Sensitive Paint 

Testing Testing Provides continuous surface pressure and or temperature 

data using a paint containing fluorescent dyes which are 

sensitive to oxygen partial pressure as well as temperature. 

Results can be integrated to determine airloads on wind 

tunnel models/components. Suitable for temperature 

mapping as well as boundary layer transition detection. 

Works in cryogenic conditions where IR thermography is not 

suitable. Both steady state and dynamic (time resolved) data 

at up to 10 kHz can be obtained. 

High-Speed Schlieren and Shadowgraph 

AT Aerothermal 

Testing 

PSP Pressure 

Sensitive Paint 

Visualizes flow density variations including shock waves and 

vortex cores. Images can be recorded at up to 100 kHz. Data 

are processed to obtain frequency spectra of density 

fluctuations at arbitrary locations in the flow, or to obtain flow 

velocity by tracking the movement of turbules. 

Background-Oriented Schlieren 

Visualizes flow density variations by measuring fluctuations in 

the position of a speckled background. Able to access areas 

of the tunnel and viewing angles which traditional schlieren 

techniques cannot. 

Particle Image Velocimetry 

PMT Pressure SC Stability and Control A method for measuring velocity in a particle-seeded flow. 

Model Test HA High Angle-of-Attack A double pulsed laser sheet illuminates a two-dimensional 

Testing particle field. 

Non-Optical measurement techniques available 

Advanced Force Balance 

AETC facilities maintain a comprehensive inventory of 

balances for force and moment measurements including 

traditional six-component balances over a wide load range, 

floor balances for semispan models, rotating balances for 

turbomachinery, and specialized balances for many unusual 

P Propulsion System PT Performance applications. In addition to balance services provided during 

Testing Testing AETC tests, balance loans may also be available. 

JET Jet Effects Testing Dynamic Data Systems 

AETC facilities maintain high speed data systems suitable for 

excitation and readout of many types of unsteady pressure 

and force sensors and can accommodate tests requiring a 

large number of channels of unsteady data. 

Other techniques, such as Oil-Film Interferometry, 

Planar Laser Induced Fluorescence, and Femtosecond 

laser Electronic Excitation and Tagging are also 

SG Shadowgraph SS Semi-Span available upon request. 

Flow Visual Testing 

For a full list of test capabilities and specialized test techniques please visit us at: 

www.nasa.gov/aeroresearch/programs/AAVP/AETC

The Right Facility or Contact Test Technology Manager, James Bell - james.h.bell@nasa.gov at the Right Time