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NASA-CR-177349 

19850022702 

A Reproduced Copy 

OF 

Reproduced for NASA 

by the 

NASA Scientific and Technical Information Facility 

FFNo 672 Aug 65 

111111111111111111111111111111111111111111111 

NF01720 

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NASA CONTRACTOR REPORT 177349 . 

(NlSA-CR-177j49) FOSELAliE tPiASII EFfEC1S ON N85-310 lS 

BSBl B~TCB SYSTlnS LEoeiag Ve~tol Co., 

PbiladelJ:bid, Pa.) 25b p UC 11:t/HF AJ 1 

CSCL 01A Unclas 

FUSELAGE UPWASn EFFECTS ON RS~\ ROTOR SYSTEMS 

J. Cowan 

L. Dadone 

CONTRACT N.1.\S2- 11307 

August 1985 

G3/02 24913 
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NASA CONTRACTOR REPORT 171349 

FUSELAGE UPWASH EFFECTS ON 

RSRA ROTOR SYSTEMS 

J. Cowan 

L. Cadone 

Boeing Vcrtol Company 

Philadelphia, Pennsylvania 

Prepared for ~es Research Center 

under Contract NAS2-ll307 

August ]'185 

Nanonal Aeronautics and 

Space Admlnlstranon 

Am~ Research Centor 

Moffett Field. California 94035 

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2.0 

3.0 

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TABLE OF CONTENTS 

LIST OF FIGURES. 

LI ST OF TABLES • • 

LIST OF SnmOLS • 

5 tJIttMAR y. • • 

INTReJDUCTION 

. . . 

. . . . .. 

• • • iii 

· . . • viii 

· . . . ix 

· . 1 

2 

A GENERAL DESCRIPTION OF FUSELAGE/WINGjENGINE UPWASH 

EFFECTS AND OF THEIR MODELING. • • • • • • • 4 

DESCRIPTION OF THE CODES USED. • • • • • • 7 

4.1 The a-65 Rotor Performance Analysis 4.2 The C-60 Dynamics Loads Analysis 4.3 The B-21 Rotor/Walte/Fuselaqe Interaction Processor 

4.4 The TEA-230 Potential Flow Analysis 

DESCRIPTION OF RSRA CONFIGURATIONS AND FLIGHT 

CONDITIONS • • • • • • • • • • •• • • • 

POTENTIAL FLOW l10DELS OF THE RSRA. • • • • 

DESCRIPTION OF MAIN ROTOR CHARACTERISTICS. • 

DISCUSSION OF THE EFFECTS OF FUSELAGE/WING/ 

ENGINE UPWASH ON TdE PERFORHANCE AND LOADS 

OF THE RSRA ROTOR. • • • • . • • • 

CONCLUSIONS AND RECOMMENDATIONS. 

REFERENCES 

APPENDICES 

APPENDIX A Potential Flow Model Coordinates 

APPENDIX B Tabulation of upwash Values • 

APPENDIX C Supplementary Loads Analysis Comparisons· • • • • • • • • 

APPENDIX D Surface Plots. . • • • • • • 

ii 

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12 

17 

26 

27 

74 

7S 

76 

77 

••• 179 

• 207 

240 

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Figure 

Number 

3-1 

4-1 

4-2 

6-1 

6-2 

6-3 

6-4 

6-5 

6-6 

6-7 

6-8 

8-1 

8-2 

8-3 

8-4 

8-5 

LIST OF FIGURES 

Single-Rotor Upwash Calculation Procedure. • 

Comparison of Measurod and Calculated Rotor 

Per form.ance. . . . • . . . . . . . • . . . . . . . . Comparison of Measured and Calculated Lift per unit 

Span . . . . . . . . . . . . . . . . . . . • 

Potential Flow Model of the RSRA Fuselage. . . . . . Potential Flow Model of the RSRA Fuselage. Top and Side Views • • • • •• ••••••• 

Potential Flow Model of the RSRA Fuselage with 

Auxiliary Wings. • • . • • • • • • • • • • • • 

Potential Flow ['fodel of the RSRA Fuselage with 

Auxiliary Wings. Top and Side Views • • •• • 

Potential Flow Model of the RSRA Fuselage with 

Auxiliary Engines ••••••••••••••• . . . Potential Flow Model of the RSRA Fuselage with 

Auxiliary Engines. Top and Side Views •••• . , . Potential Flow Model of Complete RSRA 

Configuration •••••••••• 

Potential Flow Model of Complete RSRA 

Configuration. Top and Side V\ews .•• 

Effect of RSRA Upwash on Calculated Rotor Power. 

Effect of RSRA Upwash on the Calculated 

Equivalent Lift to Drag Ratio. • • • • • • • • • 

Effect of RSRA Upwash on the Calculated Elastic 

Twist Deflection at the Tip - Vibratory Component. . . . . . . . . . . . . . . . . • . . 

Effect of RSRA Upwash on the Calculated Fourth 

and Eight Harmonics of Rotor Thrust. • • • • • 

Effect of RSRA Upwash on the Calculated Fourth 

and Eight Harrn\mics of the Rotor Torque. • • • 

iii 

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5 

9 

10 

18 

19 

20 

21 

22 

23 

24 

25 

33 

34 

35 

36 

37 
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Figure 

Nwnber 

LIST OF FIGURES 

8-6 Variation of Equivalent Lift to Drag R~tio with 

Flight Velocit¥ from Loads Analysis. Rotor 

Lift, Gross We~ght, and Rotor Radius are Held 

Constant. . . . . . . . . . . . . . . . . . . . .. 38 

8-7 Variation of pitch Link Load Vibratory Amplitude with Flight Velocity from Loads Analysis. Rotor 

Lift, Gross Weight, and Rotor Radius are held 

Constant. . . . . • . . . . . . . . .. ..•.. 39 

8-8 Variation-of Flap Hinge Vertical Shear Vibratory Amplitude with Fli9ht Velocity from Loads 

Analysis. Rotor L~ft, Gross Weight, and Hotor 

Radius are Held Constant. • • • • • • • • • • • •• 40 

8-9 Variation of Vertical Hub Force Fourth HaI~onic 

Amplitude with Flight Velocity from Loads 

Analysis. Rotor Lift, Gross Weight, and Rotor 

Radius are Held Constant. • • • • • • • • • • • •• 41 

Variation of Equivalent Lift to Drag Ratio with 

Flight Velocity from Loads Analysis. Rotor Lift, 

Gross Weight, \ying Lift, and Rotor Radius are 

Held Constant. ~ • • • • • • • • • • • • • • • •• 42 

8-10 

8-11 Variation of Pitch Link Load Vibratory Amplitude with Flight Velocity from Loads Analysis. Rotor 

Lift, Gross Weight, Wing Lift, and Rotor Radius 

are Held Constant. •• • • • • • • • • • • • • •• 43 

8-12 Variation of Flap Hinge Vertical Vibratory P~plitude with Fli9ht Velocity from Loads 

Analysis. Rotor L~ft, Gross Weight, Wing Lift, and Rotor Radius are Held Constant. • • • • • • 44 

8-13 Variation of Vertical Hub Force Fourth Harmonic 

Amplitude with Flight Velocity from Loads 

Analysis. Rotor Lift, Gross Weight, Wing Lift, and Rotor Radius are Held Constant. • • • • • • •• 45 

8-14 Variation of Equivalent Lift to Drag Ratio with 

Flight Velocity from Loads Analysis. Rotor Lift, Gross Weight, and Equival~nt Flat Plate Area are 

Held Constant. •••••••••••••••••• 46 

8-15 Variation of pitch Link Load Vibratory Amplitude with Flight Velocity from Loads Analysis. Rotor 

Lift, Gross Weight, and Equivalent Flat Plate 

Area are Held Constant. • • • • • • • • • • • • •• 47 

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Figure 

Number 

LIST OF FIGURES 

8-16 Variation of Flap Hinge Vertical Shear Vibratory Amplitude with Flight Velocity from Loads 

Analysis. Rotor Lift, Gross Weight, and 

Equivalent Flat Plate Area are Held Constant.. 48 

8-17 Variation of Vertical Hub Force Fourth Harmonic 

Amplitude with Fli~ht Velocity from Loads 

Analysis. Rotor Llft, Gross Weight, and 

Equivalent Flat Plate Area are Held Constant.. 49 

8-18 Variation of Equivalent Lift to Drag Ratio with 

Disk Loading from Loads Analysis. Flight Velocity and Rotor Radius are Held Constant.. • • • 50 

8-19 Variation of Pitch Link Load Vibratory Amplitude with Disk Loading from Loads Analysis. Flight Velocity and Rotor Radius are Held Constant.. • • • 51 

8-20 

8-21 

8-22 

8-23 

8-24 

8-25 

Variation of Flap Hinge Vertical Shear Vibratory Ampli tude \/i th Disk Loading from Loads Analysis. Flight Velocity and Rotor Radius are Held 

Oonstant. . . . . . . . . . . . . . . . . . . . .. 52 

Variation of Vertical Hub Force Fourth Harmonic 

Amplitude with Disk Loading from Loads Analysis. Flight Velocity and Rotor Radius are Held 

constant.. ................. 53 

Variation of Equivalent Lift to Drag Ratio with 

Wing Lift from Loads Analysis. Rotor Lift, 

Flight Velocity, and Rotor Radius are H~ld 

Constant. . . . . . . . . . . . . . . . . . . . 

Variation of Pitch Link Load Vibratory Amplitude with \ving Lift from Loads Analysis. Rotor Lift, 

54 

~~~;~~n~~lO~i.ty: .an.d ~o.to: ~a~i~s. a:e. H.el.d. • • •. 55 

Variation of Flap Hinge Vertical Shear Vibratory Amplitude with Wing Lift from Loads Analysis. Rotor Lift, Flight Velocity, and Rotor Radius 

are Held Constant. . • . • • • . • • • ~ • • • 

Variation of Vertical Hub Force Fourth Harmonic 

Amplitude with Wing Lift from Loads Analysis. Rotor Lift, Flight Velocity, and Rotor Radius 

are Held Constant. • . • • • • • • • • • • • • • 

v 

56 

57 
Figure 

Number 

LIST OF FIGURES 

8-26 Variation of Equivalent Lift to Drag Ratio with 

Flat Plate Area for Auxiliary Thrust from Loads 

Analysis. Rotor Radius, Rotor Lift, Gross Weight, and Flight Velocity are Held constant. • • • • • •• 58 

8-27 Variation of pitch Link Load Vibratory Amplitude with Flat Plate Area for Auxiliary Thrust from 

Loads Analysis. Rotor Radius, Rotor Lift, Gross 

Weight, and Flight Velocity are Held Constant. • 59 

8-28 Variation of Flap Hinge Vertical Shear Vibratory Amplitude with Flat Plate Area for Auxiliary Tiurust from Loads ~lalysis. Rotor Radius, Rotor 

Lift, Gross Weight, and Flight Velocity are Held 

Constant. ••• . • • • • • • • • • • • • • • • 60 

8-29 Variation of Vertical.Hub Force Fourth Harmonic 

Amplitude with Flat Plate Area for Auxiliary Thrust from Loads Analysis. Fotor Radius,. Rotor 

Lift, Gross Weight, and Flight Velocity are Held 

Constant. ................... 61 

8-30 

8-31 

8-32 

8-33 

8-34 

variation of Equivalent Lift to Drag Ratio with 

Flat Plate Area for Auxiliary Thrust from Loads 

Analysis. Rotor Radius, Rotor Lift, and Flight Velocity are Held Constant. •••••••••• 

Variation of Pitch Link Lead Vibratory Amplitude with Flat Plate- Area for Auxiliary Thrust from 

Loads Analysj~. Rotor Radius; Rotor Lift, and 

Flight Velocity are Held Con~tant .••••••• 

Variation of F1.1P Hinge Vertical Shear Vibratory Amplitude with Flat Plate Area for Auxiliary Thrust from Loads Analysis. Rotor Radius, Rotor 

Lift, and Flight Velocity are Held Constant. • • 

Variation of Vertical Hub Force Fourth Harmonic 

Amplitude with Flat Plate Area for Auxiliary Thrust from Loads Anal~sis. Rotor Radius, Rotor 

Lift, and Flight Veloc1ty are Seld Constant. • • 

Variation of. Equivalent Lift to Drag Ratio with 

Flat Plate !>;rea for Auxiliary Thrust and Wing Lift from Loads Analysis. Rotor Lift, Flight Velocity, and Rotor Radius are Held Constant. 

vi 

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63 

64 

65 

66 

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Figure 

Number 

8-35 

8-36 

LIST OF FIGURES 

Variation of pitch Link Load Vibratory ~~plitude 

with Flat Plate Area for Auxiliary Thrust and 

Wing Lift from Loads Analysis. Rotor Lift, Flight Velocity, and Rotor Radius ure Held Constant .•••• 67 

Variation of Flap Hinge Vertical Shear Vibratory Amplitude with Flat Plate Area for Auxiliary Thrust and Wing Lift from Loads Analysis. Rotor 

Lift, Flight Velocity, and Rotor Radius are Held 

Constant. . . . . . . . . .. . . . . . . . . . . . . . 68 

8-37 Variation of Vertical Hub Force Fourth Harmonic 

Amplitude with Flat Plate Area for Auxiliary Thrust and Wing Lift from Loads Anal¥sis. Rotor 

Lift, Flight Velocity, and Rotor Rad1us are Held 

Constant. . . . . . . . . . . . . . . . . . . . . . . 69 

8-38 Variation of Equivalent Lift to Drag Ratio with 

Rotor Radius from Loads Analysis. Flight Velocity and Disk Loading are Held Constant. • • • • • • • • • 70 

8-39 Variation of pitch Link Load Vibratory Amplitude with Rotor Radius from Loads Analynis. Flight Veloci ty and Disk Loading are Held Constant.. • • 71 

8-40 Variation of Flap Hinge Vertical Shear Vibratory Amplitude with Rotor Radius from Loads Analysis. Flight Velocity and Disk Loading are Held 

Constant. . . . . . . . . . . . . . . . . . . . . . . 72 

8-41 Variation of Vertical Hub Force Fourth Harmonic 

Amplitude with Rotor Radius from Loads Analysis. Flight Velocity and Disk Loading are Held 

Constant. • • • • • • • • • • • • • • • • • • • • • • 73 

vii 
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Table 

Number 

LIST OF TABLES 

I RSRA Upwash Study Flight Conditions • • • . • • 14 

I I RSRA Up\lash Study Definition of Key Parameter 

Variation • • • • • • • • • • • • • • • • • • • 15 

III Values of Key Parameters. • • • • • • • • • • • 16 

IV Flight Conditions and Potential Flows Models for 

Loads Analysis Illustrated Comparisons ••••••• 30 

~lL-..-_ viii 

• 
D 

DE 

fe 

LIST OF SYMBOI.S 

Blade element drag coefficient, drag/qc 

Blade element lift coefficient, lift/qc 

Blade element pitching moment coefficient about the 

quarter chord, moment/qc 2 

Rotor diameter, ft 

Rotor equivalent drag, rotor power/V-X, pounds 

Flat plate equivalent area, ft2 

FZF Vertic~l hub force fourth harmonic amplitude, lbs 

GW Gross Weight, pounds 

7.- Wing lift, pounds 

M Mach number 

P Auxiliary thrust, pounds 

PLL Pitch link vibratory load, lbs 

q 

R 

T 

Dynamic pressure, ~V~ 

nth harmonic of rotor torque, ft-pounds 

steady or average rotor torque, ft-pounds 

Blade radius, ft 

Vertical corponent of rotor thrust, pounds 

nth harmonic of rotor thrust, pounds Also, particular value of T in Tables II and III, 

pounds 

To Steady or average rotor thrust, pounds 

UP Nondimensional difference between out-of-disk 

velocity component in the presence of fuselage/ wings/engines and out-of-disk velocity component in the absence of fuselage/wings/engines 

UT Nondimensional difference between in-disk 

chordwise velocity component in the presence of 

fuselage/\dngs/engines and in-disk chordwise 

veloci ty co:nponent in the absence of fuselage/ wings/engines 

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V 

VT 

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X 

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6UT 

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LIST OF SYHBOLS 

(continued) 

Flight velocity, ft/sec or knots 

Rotor tip speed, ft/sec 

Fuselage station in fuselage coordinate system, 

Rotor propulsive force, pounds 

Nondimensional rotor propulsive force,o X/qD2 a 

Buttline in fuselage coordinate system, in 

Waterline in fuselage coordinate system, in 

Rotor shaft angle, degrees 

Same as UP but not nondimensionalized by rotor 

speed, ft/sec 

Same as UT but not nondimensionalized by rotor 

speed, ft/sec 

Nondimensional flight velocity, V/VT 

Rotor solidity 

Blade azimuth angle, degrees 

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1.0 SUMMARY 

The effects of RSRA fuselage configurations .on rCltor performance and loads have been 9Uantified analytically b¥ means of 

currently available potent1al flow and rotor analys1s me~~ods. 

Four configurations of the Rotor Systems Research Aircraft 

(RSRA) were considered in this study. They were: 

1) Fuselage alone (conventional helicopter) 2) Fuselage with auxiliary propulsion 3) Fuselage with wings (auxiliary lift) . 4) Fuselage with both auxiliary lift and propulsion 

The rotor system investigated was identical to a CH-47D front 

rotor e>:cept that it had four instead of three blades. Two. 

scaled-down versions of the same rotor were was also analyzed 

to determine the effect of rotor scale on the fuselage upwash effects. 

The flight conditions considered for the upwash stud¥ are discussed. The potential flow models for the RSRA conf1guration, with and without the wings and the auxiliary propulsion system, 

are presented. The results of fuselage/wing/propulsion syste~ 

upwash on performance and loads are also presented. 

The plethora of data resulting from this study reflected the 

existence of complicated flow interactions and did not lend 

itself to straightforward interpretation ill al!. cases. ~lore 

often than not though, neglecting fuselage upwash causes an 

underestimation of performance and an underestimation of loads. 

The appendices contain potential flow model coordinates, 

upwash vlaue tabulations, loads analysis comparisons ~upplementary to those shown in figures, and examples of 

surface plots. 

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2.0 INTRODUCTION 

The proximity of the fuselage to the rotor of a heticopter has 

a significant effect on the flow p.nvircr.ment at the rotor. Rec~nt flight tp-sts (particula~ly ~~e YUH-61A fliqht test 

experience) have shown that rotor/fuselage separ~~icn is on~ of 

the dominant parameters in dete~ining rotor-induce6 vibratory loads, with associa.ted detrimelltal effel;ts l'cmging from pilot/ 

passenger discomfort to reduced fatigue life of blades and 

control system, and to a possible degradation of pe.£orrnance alld rotor limits. The fuselage prox.'.mi ty effects would be 

further magnified on helicopters t:tilizing auxi.liary means of 

lift and propulsion because of the addi~i~nal flew changes introduced by wings and fans. 

The Rotor ~yste~ Research Aircraft (RSRA) is the ideal syste~ 

to ex~lore combinations of rotors with auxiliary lift an.d auxil~nry propulsion devices, but the underst~lding of the 

results of a flight test program would be strongly influ~nced 

by the degree to which mutual interferenc~ effects cetwc~n 

helicopter components can be quantifie~. 

The analytical methods necess~ry to aEsess fus:elage, wing, and 

propulsion system effects on the fl~w field have been suff~­

ciently improved to allow calculations of thi~ n~ture to be 

carried out on computers having an adequate capacity. At: the 

same time ~otor loads and ?erf~rmance analy~is methods have 

been developed which successfully predict the charac~~ri3ti=~ 

of helicopter rotors at all but the more extr~me flight conditions. 

The cornbinationof three-dimensional potential flow and rotor 

loads/performance analysis methods has been the subject of research during recent yea~s. The preliminary results have b~en 

encouraging, and data ha~dling procedur~s have been developed wl,ich have considerably reduced the iT~i:erface problems between 

potential flow and rotor analysis codes. 

During this study, an approximation to the effect!: of 

fuselage/wing/engine proximity was dete~ined by the coupiing of a th£ee-dimensional potential flow program with rotor loadp and performance analyses. The approximation was made in order 

to asse~s the character of these effects on loads and performance. A close approximation would have involved an iterative 

process - determining the influence of fuselage/wing/engine proximity 0:':, loads and performance, determining' the influence 

of rotor-induced downwash on the potential flow about the structur~s, 3nd repeating the cycle. This study was limited to 

using only the first step, determining the initial influence of 

structural proximity ~n th~ rotor environment. The iterative 

process was outside thP. scope of the present s~udy. 

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Previous efforts to determine the effects of fuselage proximity 

on rotor loads and performance were limited by the crudeness of 

the potential flow models or the rotor analyses. Two of these 

efforts were reported by Rahnema (Reference 1) and by Bain and 

Landgrebe (Reference 2). Rahnema investigated the alleviation 

of rotor loads with calculations that used only a single point 

source in a uniform free stream to model the flow about a . fusleage. Bain and Landgrebe used a lifting line for the wing of a compound helico~ter. The'present study, by contrast, uses 

a fully three-dimenslonal panel method with wing vorticity distributed chord\dse to model the flow about aerodynamic bodies. 

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3.0 A GElffiRAL DESCRIPTION OF FUSELAGE/WING/ENGINE UPWASH 

EFFEC'rS AND OF THEIR l>10DELING 

Although isolated rotor teots and calculations are most often 

employed in the definition of advanced rotor systems, it is 

understood that the final success of a rotor system depends on 

its integration with fuselage components. In particular, test 

and theory have shown that the placement of ~~e rotor with respect to the fuselage of a helicopter introduces changes in the 

rotor flow field wh1ch must be accounted for to determine realistic load and performance levels. 

The presence of substantial lifting elements on the fuselage and the effect of auxiliary propulsion devices is very likely 

to increase the lrifluence of the fuselage upwash on rotor per- formance and loads, making it even more critical that well doc- \~ented rotor placement ~idelines be established. Estabishinq these guidelines is outslde the scope of the present study, but such establishing must be based on analyses such as those 

reported herein or data gathered from tests. 

The overall effects of fuselage/wing/engine upwash on a rotor 

were the object of this investigation. Considering only a single blade element, the structure induces an increment to the 

velocity component normal to the local free stream which would 

exist if no other structures were near the rotor. This 

increment changes the local angle of attack and, therefore, the 

airloads, flapping, and stresses. 

The flow about three-dimensional bodies can be evaluated by computational potential flow methods, as well as methods 

involving more fund~ental, and therefore more complex and 

expensive, approaches. In particular, the singularity panel methods are the simplest and least expensive fot 3~n flow. 

They are adequate for the present purpose, since the effects of 

viscosi ty and \10rtici t··, neglected by ~uch methods, are 

significant only close" to the fuselage/wings/engines, not in 

the off-body region where the rotor blades are located. 

To obtain a 3-D potential flow solution with TEA-230 (Rcf~rence 3), a panel method, the surface of a body is approx- imated by a number of flat, or nearly flat surfaces (panels), 0 

where the size of the panels is dictated by th~ local surface 

curvature and by t.he n(~ed for accuracy in the calculated surface velocities. A potential °Zlow solution for a given body is 

then obtained b} ~rescribing, among other conditions, the requirement that there be no flow through the panels. Local velocities are then estimated at the centroid of each panel and 

at any required point off the body. 

Figure 3-1 illustxates thP. overall logic in carrying oat rotor/ 

fuselage upuash interaction calculations. The rotor analysis 

program shown in the diagram is the B-65 perform~~ce code, Reference 4. The C-60 loads analysis, Reference 5, can be introduced in the same way. 

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IN: TRIM 

CONDITIONS 

OUT: PERFORMANCEA"!:; 

FLAPPWG 

IN: TRIM COIJDITIONS. 

UPWASHDATA 

OUT: PERFORMANCE, 

FlAI'PItlG. A~m ROTOR 

WAKE 

... 

1)..21 

IN: BLADE FLAI'VING 

AP~GLES AIm GEOMETRY 

OUT: coonDI N \YES Of 

OFF·BODY POINTS IN 

FUSELAGE COORDINATE 

SYSTEM 

) 

TEA·2llJ 

114: FUSELAGE GEOMETRY, 

OFF·CODY LOCATIOf.lS. 

FLIGHT CONDITIONS 

OUT: OfF·BODY VELOCITIES 

CHANGE CYCLIC PITCH It--..... 

GGS 

IN: TAIM CONDITIONS 

AND UPVlASH DATA 

OUT: PERFORMANCE AND 

FLAWING 

WAKE . CALCULATIONS: & ROTOR ON FUSELAGE 

TAPE OOWNWASH EFFECTS 

Figure 3-1. Single Rotor Upwash Calculation Procedurd 

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IN: ROTOR GEOMETRY AND 

POSITION DATA, UfWASH 

VELOCITIES 

OUT: AU, AP~D AUT 

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The process is started with isolated rotor trim conditions. 

The initial blade flapping schedule is used by the B-21 processor code to calculate the coordinates of blade computation points in the fuselage coordinate system. The off-body point coordinates are then input into the 3-D analysis (TEA-230) and 

off-body velocities ~re calculated. The B-21 code converts the 

off-body velocities into incremental rotor velocities which z.re 

introduced into B-65 or C-60. Finally, B-65 or c..:-60 is run 

until a solution is obtained which satisfies the required trim 

in the presence of the fuselage u~wash velocities at the blade 

computation points. The process 1S repeated only if substantial changes in blade flapping angles take place. 

The mani~ulation of output from one program into input for 

another 1S performed automatically by the B-21 code. The only manual operations necessary are entering some of the B-65 or 

C-60 output into B-21 input, merging the B-21 output into 

TEA-230, and merging some of the TEA-230 output into the final 

B-21 input. 

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4.0 DESC~! .... orION OF THE CODES USED 

4.1 The B-65 Rotor Performance k~alysis 

The Rotor Performance Analysis, B-65, is described in Reference 

4. The code was developed at Boeing Vertol. The basis for the 

code is a model of the wake trailed by each blade, which wake 

is represented by 9roups of straight vortex segments with linearly varying vort~city from one end to the other of each segment. A root and a tip vortex are rolled up after a fixed 

azimuthal interval (1/8th of a revolution) at a radial location 

which is determined from the instantaneous spanwise blade loading (Betz criteria). The vortex sheet trailed by each blade is 

modeled by a system of vortices identified as the near-wake, 

attached to the blade quarter chord line and trailed 1/24th of 

a revolution (A~ = 15°), and a mid-wake, which extends for two 

additional time intervals (A~ = 30°) beyond the near-wake. 

As the B-65 code subdivides a rotor blade into 13 spanwise segments of equal length, cutout to tip, the vortex sheet trailed 

by each blade is represented by 13 horseshoe vortices. Except for the initial Betz rollup criteria which set the spanwise location of the tip vortices, the wake model is otherwise rig- id, and its displacement is a combination of flight kinematics 

with a uniform induced downwash velocity. 

Blade elastic properties are represented by a modal approach. Two flap bending and one torsion mode are used to model the 

elastic properties. The aerodynamic formulation, based on a 

lifting line system, includes an approximation of unsteady effects, dynamic stall delay, radial flow, reverse flow, and 

three-dimensional tip relief effects. 

The sectional characteristics are obtained by look-up and interpolation of tables of two-dimensional airfoil data com~iled 

from experimental or analytical sources. The tabulated a~rfoil 

characteristics are listed in the following sequence: 

(a) 

(b) 

Lift Coefficient, Cf . Presented as a function of angle of 

attack at flxed Mach number levels, for angles from 0° to 

20°, and from -20° (340°) back to 0° (360°), for Mach numbers from r1 = 0.0 to M = 1. O. Lift data from 20° to 340° 1S simulated by equations based on test data for the NACA 

0012 airfoil, Reference 4. These equations are indepen- dent of Mach nun~er as they are meant to approximate the 

high angle-of-attack flow conditions inside the reverse 

flow circle. 

Draa Coefficient, Cd. Drag is presented as a function of 

l1adi nWlilier, for f>l = 0.0 to M = 1.0, at constant angle of 

attack levels over an angle of attack range which can be 

specified in the input. Outside of the specified angle of 

attack range the drag is approximated by equations independent of Hach number and based on NACA 0012 test data. 

. .Itt 
/ 

/ 

I 

v 

(c) Pitching ~!oment coeffientr Cm. Pitching moments are 

taEulatea as a function 0 l1ach number, from H = 0.0 to M 

= 1.0, for angles of attack from 0° to 16°, and from -16° 

(344°) to 0° (360°). Equations based on NACA 0012 data 

cover the rest of the high angle of attack range. 

B-65 output consists of airload and power distributions across 

the blades at 24 azimuthal locations. It also includes the 

distribution of elastic twist and deflections at those locations. Flapping angle is output in harmonic form and the 

other distributions can be harmonically analyzed. No specific number of harmonics is modeled becaU3e flapping is determined 

by solving a differential equation for flapping angle instead 

of simply finding the Fourier coefficients of an assumed harmonic behavior. 

The accuracy of this code is reflected in Fi9Ure 4-1. In this 

figure, "Configuration 611 designates a partl.cular blade plan- form, IIBVWT" means Boeing Vertol Wind Tunnel, "svwr 256" is a 

particular wind tunnel test, f:4nd "WOZ" [!'leans "wind-off zero." 

4.2 The C-60 Dynamics I&ads Analysis 

The Dynamics Loads Analysis was developed at Boeing Vertol by the Rotor Dynamics Group. A detailed description of C-60 can 

be found in Reference S. 

C-60 uses a lumped-mass representation of a rotor blade, including up to 25 masses. The elastic properties are repre- sented by elastic, massless rods connecting the masses. The 

airloads are evaluated on a relatively coarse radial and 

azimuthal grid from .... hich dense airload distributions can be 

generated by intepolation and harmonic analysis. 

Although C-60 has provisions for a trailed vortex sheet, satisfactory air:oads have been calculated by means of induced velocities from the root and tip vortices only. 

Without the limitations of the modal approach of B-65, the C-60 

analysis can evaluate the motions and deflections of a rotor 

blade in .... hatever complexity the dynamics and aerodynamics of 

the problem dictate. Blade and control loads can be then defined and analyzed in detail .... ith the harmonic content. 

C-60 output consists of airload and internal load distributions 

across the blades at 24 azimuthal locations. It also includes 

pitch link and hub loads. Ten harmonics of the blade can be 

and were modeled, in order to obtain the highest definition of 

the above distributions. The accuracy of this code is 

reflected in Figure 4-2. 

8 

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BVWT TEST DATA .... eORRECTi:D FOR I0 THRUST 4 TORQUE 

-I-

.014 WOZ 

Z 

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RUN 359 

\11. 0.4 

.00d X • 0.0371 

V • 700.0 FPS 

RADIU! • 5.052 FT 

CONFIGURATION 6 

POWER eOEFFleIE~T ee,,) 

Figure 4-1. Comparison of Measured and Ca/culate<.f Rotor Performance 

9 
, 

, 

( ----,-

z 

~ 

0.. 10 rn 

t: 

H-34 ROTOR 

as • -5-

THRUST • 8486 lB 

X • 629 LB 

V • 150 KNOTS 

NACA 0012 AIRFOIL 

16.4-INCH CHORD 

.... 

~ O~--~~~--~--~~~~--~---+--~--~----~--+-~ 0 30 

5 -10 L 

180 210 240 270 300 330 360 

AZIMUTM (OEG.) 

Figure 4-2. Comparison of Measured and Calculated Uft per Unit Span 

10 

• I • 

, 

!~ I 

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~~,.! .... ~ .......... r-~ -'_ ... ,. ~ -' .• ' , , ' ,; I ,'J .~ \ '. ," .... ,.: ..... -, ',,' '< <~. I' " ''." \' .... :." ' -, ' " •• ' t ~,. ' ..... ~,.., 4-'..... ,", :,,~ I • ' , '\',", " ' ... ,.. • - ., ' ~ '. 

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4.3 The B-21 RotorlWake!Fuselage Interaction Processor 

The B-21 RotorjWake!Fuselage Interaction Code was developed at 

Boeing Vertol. This code carries out all interface c~lculations necessary to couple a 3-D potential flow analysis, in 

particular TEA-230, with a rotor performance or loads analysis. 

B-21 takes the flapping angle Fourier coefficients from B-65 

output plus the rotor geometry-and finds from these the 

coordinates in the fuselage coordinate system of all blade computational points at all azimuths. These computational points 

are output from B-11 in e~actly the format required for 

off-body velocity computation by TEA-230. They are then simply merged with the on-body geometry of TEA-230 input. The 

off-body velocities as they appear in TEA-230 output then serve 

as another B-21 input without manipulation. 

4.4 The TEA-230 Potential Flow Analysis 

The three-dimensional potential flow analysis, TEA-230 (Boeing! Seattle), can simulate lifting and non-lifting bodies and engine flow. The code has provisions for on-body and off-body , velocity calculations. To obtain a 3-D potentlal flow solution 

the surfaces of the body are approxim~ted, as mentioned in Section 3, by a number of flat, or nearly flat surfaces (panels). A potential flow solution on the surface of a 9iven body is 

then obtained by prescribing, among other condltions, the requirement that there be no flow through the panels. Local velocities and therefore pressures are then estimated at the 

centroid of each panel and at any required point off the body. 

The TEA-230 analysis used in dlis study is described in detail 

in Reference 3. 

11 
, 

, 

":-- "-

,~" 

. , 

! I 

5.0 DESCRIPTION OF RSRA CONFIGURATION AND FLIGHT CONDITIONS 

A potential flow model of the RSRA fuselage\o1aS defined with 

provisions to combine the following components: 

A. The body of the fuselage, including the tail boom, 

but no tail surfaces. 

B. Wings and wing/fuselage fairing areas. 

c. Engines providing auxiliary propulsion. 

D. An approximate model of separated regions behind' 

the fuselage and engines. 

The individual and combined elements of the potential flow model were processed through diagnostic programs to verify the 

quality of the paneling. Computer-generated plots were provid- ed to document the mathematical models. 

The fuselage model was only as detailed as necessary to e~aluated upwash velocities at the main rotor. 

The matrix of operating conditions with and ~'ithout auxiliary lift, and with and without auxiliary propulsion, were defined. 

The fuselage and rotor configurations were limited to: 

A. The basic fuselage. B. The basic fuselage with one set of wings. C. The basic fuselage with auxiliary propulsion. D. The basic fuselage with wings and auxiliary propulsion. E. Three rotor diameters at one hub position. 

:uselage upwash and rotor performance calculations were carried ~ut for three rotor diameters, three gross weight levels, two 

auxiliary lift levels, four auxiliary propulsion levels, and 

:ombinations of both auxiliary lift and propulsion. All three rot~rs were set at the same height above the fuselage and, for 

the purposes of the current studr, this height was not varied 

from '~e current RSRA configurat10n since such variation ~ould 

require redesign of the RSRA. 

A summary of the computation conditions is presen.ted in Table 

I. The relationships of the parameters defining the flight condition:::; to the gross weights and fli<Jht v'elocities selected 

are shown in Table II, along with ident1fication ,of the effects 

illustrated by various comparisons among the fli9ht conditions. 

Table II is read in th~: following way: The numbers labled 

"CONDITION" refer to the 27 flight conditions. 'the numbers··", 

opposite the ker para.'1leters Gi.J, T, etc., refer to specific values; e.g., "1" 1n the row opposite "GW" means the gross weight is GW1 (flight conditions 1, 2, 5, 6, etc.). The "2" in the 

12 
"I 

'1' . 

'. 

~. 

I 

row opposite "T" means the vertical component of rotor thrust 

is T2 (flight conditions 3, 4, 5, 6, etc.). These key 

parameter values are defined in Table I I"; • 

The conditions shown in Table I were based on the relationships shown in Table II plus both the necessity of not letting the 

thrusts, gross weights, and velocities be unrealistic for the 

RSRA, and the desirability of not letting the different values 

of those same parameters be too close together, thus making the 

effects of tile differences difficult to detect. These conflicting requirements left little room for arbitrariness in the 

choices of computational conditions. 

13 
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~ ;' 

TABLE I 

RSRA UPWASH STUDY FLIGHT CONDITIONS 

GROSS VERTICAL COmONENT FLIGHT WING AUXILIARY ROTOR 

WEIGHT OF ROTOR THRUST VElOCITY LIFT THRUST DIru.~ETER 

CONDITION ~POUIlDSl ~POUN(lS~ {KNOTS} ~POUtlD$l ~POUNDSl (FEET) 

1 26.400 26.400 112.5 0 0 60 

2 26.400 26.400 162.5 0 0 60 , 3 18.333.3 18,333.3 112.5 0 0 60 

4 18.333.3 18,333.3 162.5 0 0 60 :1 .. 5 26,400 18.333.3 112.5 8.066.7 0 60 

6 26.400 18,333.3 162.5 8,066.7 0 60 

7 18.333.3 18,333.3 112.5 0 983 60 

8 18,333.3 18.333.3 162.5 0 2.051 60 

9 26.400 18,333.3 112.5 8,066.7 983 60 

10 26.400 18,333.3 162.5 8,066.7 2,051 60 

11 18.333.3 18,333.3 112.5 0 0 50 

1 12 18,333.3 18,333.3 162.5 0 0 50 

.... 13 18.333.3 18.333.3 112.5 0 983 50 .I 

or. 14 18,333.3 18,333.3 162.5 0 2,051 50 

IS 26,400 18,333.3 112.5 8,066.7 0 SO 

16 26.400 18,333.3 162.5 8,066.7 0 50 

17 26,400 18.333.3 112.5 8,e66.7 983 SO 

18 26.400 18,333.3 162.5 8,066.7 2,051 SO 

19 22.366.7 22.366.7 162.5 0 0 60 

20 22,366.7 18.333.3 162.5 4,033.3 0 60 

21 22,366.7 18,333.3 162.5 4,033.3 2.051 60 

22 18,333.3 18.333.3 162.5 0 1,025.5 60 

23 22.366.7 18.333.3 162.5 4.033.3 1.025.5 60 

24 22,366.7 22,366.7 162.5 0 0 55.2 

25 26.400 26,400 137.5 0 0 60 

26 26.400 18,333.3 137.5 8,066.7 0 60 

27 18,333.3 18.333.3 137.5 0 1.466.5 60 

.J> 

t- •. -----.-.-------.. -
'j 

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. ----. ( 

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if' "'.~ j4;p.e_ f"p . t a:r is; .t.4" .* It ,,".1 , }' Y'''; . q •... (44 e, . 

TABLE II. RSRA UPWASH STUDY 

DEFIflITION OF KEY PARAMETER VARIATION 

GW, :a T,; GVl2 :a T 2; GW3 ,. G\'I, + GW2; liW, > GW2 

2 

V2 > V, V3::1 (V, + V2)f2 

LI • GW, - T 2; Li:: LI/2 :: GW3 - T 2 

O2 • 0"1 GVlz ; 03 ::1 O'YGW3.. 

GW, mY, . 

P, ,. f. q" P2 • ft q2 P3 "!! q2 P4 " fe q3 

2 

~ LARGE DIAMETER SMALL DIAMETER L1fdEARITY CHECK "4 fl{), 

1I'4I1l:'{)tv 1 . 2 3 4 5 G 7 a 9 10 1112 1314 1516 17 111 19 20 21 22 23 24 25 2!i 27 

GW· , 1 2 2 1 , 2 2 , , 2 2 2 2 1 I 1 , 3 3 3 2 3 3 1 '12 

T I I 2 2 2 2 2 2 2 2 2 2 2 2 2 ~ 2 2 3 2 2 2 2 3 , 2 2 

V 1 2 1 2 1 2 1 2 1 2 1 2 1 2 , 2 1 2 2 2 2 2 2 2 3· 3 3 

L - - - - 1 1 - - 1 1 :- - - - 1 1 1 1- 2 2- 2 - - ,-

P - - - - --, 2 1 2 - - 1 2 - - , 2r- - 2 3 3 - - - 4 

OIA j 1 1 1 1 1 1 1 1 1 2 2 2 2 2 2 2 2 1 1 1 1 1 3 1 1 , 

EHECT OF or;; --- -- - - r--- ----- - -= - ~. 0-0 ~ or? ~ cR,) ()...Z; t:;.:O rr~ -- ~ - -1"- - '0 

VELOCITY -- -- 1--- -- -- -,-I- -... --ro 

EFFECT OF ~-.r -- I- - -- ---- ~- - <> 

DISK LOAD 

EFFECT OF o-I=-1S - -- --- .--- -0 o 0 

WWG LIFT o-r::.o -- - o ---... :;) ---£:'"0 '0 

EFFECT OF r--t--~- -- -x-----0 0 0 o----Q 

PROP FORCE o 1::-0- --- - -- - --..:.0 \1ITH LIFT 0---0 

EFFECT OF 0 r--- - - ---------"-0 

LIFT & PROP F o G G 

EFFECT OF 0 r - - - -0- olsK'iOAD:I C~ST - --v 

DIAMETER Q 0 GW· CQrJST 

0 o GW- COfJST & X::I 0 

0 I;) G\'I&L" COrJST 

Q G GW&t, • COHST & X i 0 

15 
· ..• ( C~«IIIr'\ , 

'I 

TABLE III 

VALUES OF KEY PARAMETERS 

GWI = 26,400 pounds 

GWz = 18,333.3 pounds 

GW3 = 22,366.7 pounds 

Tl .- 26,400 pounds 

T2 = 18,333.3 pounds 

T3 = 22,366.7 pounds 

VI = 112.5 kno~s 

V2 = 162.5 knots 

"13 = 137 . .5 knots 

Ll = 8,066.7 pounds 

L2 = 4,033.3 pounds 

'I 01 = 60 feet 

O2 = 50 feet 

03 = 55.2 feet 

PI = 983 90unds 

P2 = 2,051 pounds 

P3 = 1,025.5 pounds 

P4 = 1,468.5 pounds 

16 
I 

-r 

! 

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\ 

6.0 POTENTIAL FLo\~ ~mDELS OF THE RSRA 

There were four significantly different potential flow models 

used in this study: the RSRA fuselage (Figures 6-1 and 6-2), 

the fuselage with auxiliary propuleion engines (Figures 6-3 and 

6-4), the fuselage with auxiliarr wings (Figures 6-5 and 6-6), and the fuselage with both auxillary wings and auxiliary engines (Figures 6-7 and 6-8). Two more combinotions of fuselage and auxiliary wings, one with and one without auxiliary engines, were used. The wings of these were at different incidence angles. They strongly resembled the combinations in 

Figures 6-5 and 6-7. 

In all of these models the tail surfaces and engine supports 

were omitted. The cylindrical tube behind each truncated 

fuselage is used to represent, in rough approximation, the 3ft 

fuselage, fuselage boundary layer, and fuselage wake. The 

cylindrical tubes behind the engines are used to approximate the exhaust jets. 

17 

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. Figure 6-4. Potential Flow ~~del of the RSRA Fuselage with Auxiliary Wings. Top and Side Views. 

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7.0 DESCRIPTION OF MAIN ROTOR CHARACTERISTICS 

The rotor used in this study is identical .to a CH-47D front 

rotor except that it has four instead of three blades. The 

radius of this rotor is 30 feet and the chord 32 inches. The 

airfoil, from the cutout at 21% of the radius to 85% of the 

radius, is the Boein9 Vertol VR-7. At the tip, the airfoil is 

the VR-8. The airfoll of the last 15% of the blade isa linear 

transition between these two. .The VR-7 is 12% thick, the VR-8 

is 8%. The planform of the blade is rectangular. The twist is 

linear, decreasing 7.63 0 between the cutout and 85% of the 

radius and another 0.7 0 between the 85% point and the tip. For 

some of the fli9ht conditions, a 25-foot Mach-scaled version of 

the same rotor 1S used, and, for condition 24, a 27.61 foot 

rotor, also Mach-scaled, as defined in Table II. l1ach scaling here means that velocities (and therefore Mach numbers) and 

densities are conserved as lengths are changed in the scaling 

process. Therefore, airfoil shapes, disk loadings, t.wist 

angles, pressures, thicknesses as fractions of chord, and 

moduli of elasticity are conserved, but masses, lengths, forces, areas, volumes, and accelerations are not. l·tasses are 

proportional to the cube of the rotor radius, while lengths are 

proportional to the radius itself. Forces, except f'Jr weight, which is not scaled corre~tly, are proportional to the square of the radius. Areas and volumes are proportional to the 

second and third powers of the radius, while accelerations' are 

inversely proportional to the first power. In ~articular, the 

25-foot radius rotor has a 26.67-inch chord, wh1le the 

27.61-foot rotor has a 29.45-inch chord. 

26 

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, 

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/

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8.0 DISCUSSION OF THE EFFECTS OF FUSELAGEjWING/ENGlNE UPl'lASH 

ON TEE PERFORI>1ANCE AND LOAbS OF THE RSRA ROTOR 

The effects of upwash on performance is shown in Figures 8-1 

through a-so 

Figure 8-1 displays the values of required rotor horsepower determined by B-65 for the 27 flight conditions shown in Table 

I I. To keep from splitting hairs too finely, i t \~as deemed 

necessary to consider an influence due to fuselage/wing/engine upwash which changed the rotor power by less than 400 horse- ~ower to be ~estionable. Considering only r.onsequential lnfluences, 1 t appec.rs that for only Flight Conditions 2, 8, 16~ and 21 does fusela~e/wing/engine ~pwasn in~r~ase the requlred rotor power, whlle for only Fl!ght Condltlons 7, 13, 14, 

22, and 23 does the upwash decrease that power. From these 

observations one can conclude tllat, at least in general, fuse- la~e/wing/en~ine upwash increases required rotor power at high fllght veloclties when the sum of rotor and wing lift is high, while auxiliary engine upwash without wing upwash decreases the 

required power. 

Figure 8-2 displays the values of equivalent lift-to-drag ratio 

determined by B-65. If one considers h~re that differences in 

LIDE of less than 0.6 are not significant, one finds that fuselage/wing/engine upwash significantly increases LIDE for Flight Conditions 7, 13, 14, 22, 23, and 27 and significantly decreases 

LIDE for Flight Conditions 8 and 21. From these observations 

one can conclude that, in general, engine upwash can significantly influence LIDE in the presence of little or no wing upwash. One can conclude also that the engine upwash increases LIDE 

except possibly when auxiliary thrust is high. 

In comparing Figures 8-1 and 8-2 and w,lile noting that the only quantity contributing to LIDE which should change due to fuselage/wing/engine upwash is the rotor power, one should expect changes in LIDE due to fuselage/wing/en~ine upwash to be op- posite changes in rotor horsepower. ThlS indeed is the case, 

except for Flight Conditions 2 and 4, where the changes in power are slight and 'ire offset by the changes in lift and X allowed by the convergence tolerances. 

Figure 8-3 displays th(! vibratory component of the blade tip elastic twist deflection as calculated by 8-65. If one decides 

that differences in 69 less than 0.016 radians are question- able one finds fuselag§7wing/engine upwash significantly decreases 69 for Fli~ht Conditions 2, l2, l4, 19, and 27 but 

never sign~!icantlY lncreases 6a~L' It is somewhat difficult 

to find commonality in these five flight conditions, although they all involve high flight velocities or auxiliary pro- pulsion. None involve wing lift. Most of these conditions . involve reasonably high disk londing . 

, 

., 

27 

'. -~ 

~ 

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.. 
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-.. " 

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, " 

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,..l I 

, . 

, .. '. 

: ; 

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! 

/ 

r 

/ ! . 

I ' 

// : 

'j , 

Figure 8-4 displays the normalized magnitudes of the fourth and 

eighth harmonics of rotor thrust as determined by B-65. If one 

considers differences in T4/TO less than 0.014 to be insignif- icant, on~ finds that fuselage/wing/engine upwash significantly increases T</To for Flight Conditions 21 and 22 and significantly decreases it for Flight Conditions 2, 4, 6, 12, 24, and 26. 

These Flight Conditions are at medium and high flight velocities 

and usually involve disk loadings that ure not high. In parti- cular, the two flight conditions for which fuselage/wing/engine upwash increases T1/To involve a high flight velocity and reasonably low disk load~n~s. But these are the only flight conditions 

among the eight si~~ficant ones which involve auxiliarr propul- sion. The other s~x flight conditions involve no auxil~ary 

propulsion and experience decreases in T4/TO due to fuselage/ wing upwash • 

If one uses 0.014 as also the lower limit of significant differences in Ta/To, one finds that fuselage/wing/engine upwash significantly increases Ta/To for Flight Conditions 5, 8, 13, 19, 21, 22, and 23 and significantly decreases it for Flight Conditions 2, 6, 14, 16, 18, 24, and 25. These 14 flight conditions have little in common except that most of them involve 

the highest flight velocity. Why fuselage/wing/engine upwash increases or decreases Ta/To is not clear at all. 

Figure 8-5 displays the normalized magnitudes of the fourth and 

eighth harmonics of rotor torque as determined by B-6S. A comparison of differences in Q4/QO due to fuselage/wing/upwash show little correlation with the key parameters of the flight conditions or the RSRA potential f!ow models, except that the 

largest differences occur at high flight velocity. If one considers differences in Qs/Qo less than 0.022 to be insignificant, one finds that fuselage/win~/engine upwash significantly increases Qs/Qo for Flight Condit~ons 7, 9, 13, and 17 and sig- nificantly decreases it for Fli~ht Condition 22. The flight conditions for which Qa/Qo is s~gnificantly increased are all 

at the lowest flight velocity and all use auxiliary propulsion. Fli~ht condition 22, by contrast, uses the highest fli9ht ve- loc~ty and, by comparison, also uses auxiliary propuls~on. 

However, other flight conditions using auxiliary propulsion and 

high flight velocity do not experience significant changes in 

Qs/Qo due to fuselage/wing/engine upwash. 

The effects of upwash on loads is shown in Figures 8-6 through 8-41. In each figure, the solid curve inuicates the i~olated 

rotor, the dashed curve the rotor influenced by upwash induced 

by fuselage and/or auxiliary wings and/or auxiliary engines. 

The figures are grouped according to the independent variable 

and the constant parameters. Figures 8-6 through 8-9 show 

functions of flight velocity in which the upwash (if any) is 

caused by only the RSRA fuselage. Figures 8-10 though 8-13 arc 

similar except that the infll\ence of the wings has been added. 

28 

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, 
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r~ 

f ' 

_~or-, "m_;;-__ ~~-.~~;--::7:::::::7:.:::::::::::-r:= .. __ .. ___ ._.·7-

Figures 8-14 through 8-17 are like Figures 8-6 through 8-9 except that the influence of the auxiliary engines has been added. Figures 8-18 through 8-21 show functions of disk loading in which the upwash is caused by only the fuselage. Figures 8-22 through 8-25 show functions of wing lift. Figures 8-26 

through 8-29 show functions of the flat plate area for the 

thrust from the auxiliary engines. Figures 8-30 through 8-33 

are similar but with wing lift added. Figures 8-34 through 8-37 show functions of auxilial;y engine flat plate area ana. 

wing lift as both increase together. Finally, Figures 8-38 

through 8-41 show functions of rotor size at a constant disk 

loading. Table IV lists the flight conditions and potential flow models for each of the above groups of figures. 

Another grouping can be considered in which the figures of each 

group display the same dependent, as opposed to independent, variable. Figures 8-6, 8-10, 6-14, 8-18, 8-22, 8-26, 8-30, 

8-34, and 8-38 display the variation of equivalent lift-to-drag ratio with several different parameters and at many different 

flight conditions. Fi9Ures 8-7, 8-11, 8-15, 8-19, 8-23, 8-27, 

8-31, 8-35, and 8-39 dlsplay th~ variation of pitch link load 

vibratory amplitude with the same parameters and at the same 

flight conditions. Fi9Ures 8-8, 8-12, 8-16, 8-20. 8-24, 8-28, 

8-32, 8-36, and 8-40 dlsplay tile variation of flap hinge vertical shear vibratory ~lplitude while Figures 8-9, 8-13, 6-17, 

8-21, 8-2S, 8-29, 8-33, 8-37, and 8-41 display the variation of 

FZF, the vertical hub force fourth harmonic amplitude. 

It will be most instructive to discuss these figures according 

to this last grouping, beginning with the equivalent liit-to-drag ratio. 

Fuselage upwash alone generally slightly increases LIDE regard- less of flight velocity (Figure 8-6) or disk loading (Figure 8-18). Wing plus fuselaCJe upwash slightly decreaf.es L/DE regardless of flight veloclty (Figure 8-10), but generally increases it at low values of wing lift (Figure 8-22). There is 

a significant increase in LIDE due to the upwash of the fuselage and auxiliary engines for all flight velocities (Figure 8-14) and for all values of the flat plate area opposing the 

auxiliary engines (Figure 8-26). The upwash of fuselage, wing, and auxiliary engines generally increases L/DE despite variation in flat ~late area (Figures 8-30 and 8-34) or wing lift 

(Figure 8-34). There appears to be little effect due to fuselage upwash alone if the rotor size varies but di!;k loading remains constant (Figure 8-38). , 

,-, 

These results are not identical to those determined by B-65. 

The primary reason for the differences is probably the fact 

that the C-60 loads analysis performs calculations considerably different from those in the B-65 performance analysis. The 

differences in these calculations were outlined i.1 sections 4.1 

and 4.2. 

29 

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FIGURES 

0-6 through J-9 

8-10 through 8-13 

8-14 through 8-1l 

8-18 through 8-21 

8-22 through 8-25 

8-26 through 8-29 

8-30 thr0~gh 8-33 

6-34 througn 8-37 

8-38 through 8-41 

*Fusel~ge only 

-- )" 

TABLE IV 

" FLIGHT CONDITIONS AND POTENTIAL flOW MODELS 

FOR LOA~ ANALYSIS ILLUSTRATED COMPARISONS 

**Fuselage and wing only 

FLIGHT CONDITIONS 

1 

5 

7 

2 

4* 

4* 

6*lt 

4* 

2 

2 

6 

8 

4 

6 

8 

10 

10 

12 

25 

26 

27 

19 

20 

22 

23 

23 

24 

_ .•. _---_._. __ . --"-

POTENTIAL flOW ~100El 

Fu:elage only Fuselage and wing Fuselagp. and engines Fuselage only Fuselage and wing fuselage and engines Fuselage, wing, and engines Fuselage, wing, and engines Fuselage only 

"~ 

-:;1 

] 

1 

A. 

I 

; 
'. 

'I 

I ... _.-

l 

In contrast to its effect on LIDE, fuselage upwash alone increases the pitch link load vibratory amplitude significantly 

at high flight velocities (Figures 8-7 and 8-19). The fuselage and engine upwash together produce the same result if the engines are providing most of the forward thrust (Fi~'r~s 8-lS 

and 8-~7), The fuselage-plus-wing upwash increases ~~~ PLL 

amplitude at all flight velocities (Figure 8-11), and the addi- tio~ of the engines does not generally change this result 

(Figure 8-31). The fuselage-plus-wing upwash alone increases 

the PLL amplitude at all values of wing lift (Figure 8-23). The addition of engines has the same effect, generally, if the 

.ling lift and engine thrust increase together (Figure 8-35). With the fuselage alene causing upwash, the PLL amplitude in- . creases quickly with rotor size (Figure 8-39). 

The effects of upwash on the vertical shear vibratory amplitude 

at the flap hinge are somewhat similar to the effects on L/DE. 

The fuselage upwash alone increases the vibratory amplitude at 

all flight velocities (Figure 8-8), all disk loadings (Figure 8-20), and all rotor sizes (Figure 8-40). The addition of up- wash from the wing decreases the amplitude at all flight velocities (Figure 8-12) and all rotor if the wing lift is high, but not otherwise (Figure 8-24), The fuselage-plus-engine up- wash ~enerallv increases the amplitude at high but not at low veloc~ties (Figu~e 8-16) and then only when the aUAiliary thrust is large (Figure 8-28). The upwash from the complete· 

RSRA configuration generally increases the flap hinge vertical 

shear vibratory amplitude (Figures 8-32 and 8-36), at least at 

high values of auxiliary thrust. 

The vertical hub force ivurth h~rmonic amplitude (FZF) is decreased by fuselage upwash at high flight velocities (Figure 8-9). When wing upwash is added FZF is increased at all flight velocities (Figure 8-13) but not all values of wing lift (Figure 8-25). The fuselage-plus-engine upwash decreases FZF at 

all flight velocities (Fiyure 8-17) and all value~ of auxiliary thrust (Figure 8-29). The upwash from the fuselage alone decreases FZF for all values of di~k loading (Figure 8-21) and 

for all rotor sizes (Figure 8-41). The upwash from the complete configuration de~reases FZF at high values of auxiliary thrust when the wing lift is a!.so high (Figures 8-33 and 8-37). 

It should be noted at this point that the flight conditions 

labeled "LINEARITY CHECK" in Table II show that the results in 

Figures 8-~ ~1rough 8-41 are, in general, highly nonlinp.ar. This nonlinearity is most promin~nt in the variation of flap hinge vertical shear vibratory ,ullpli tude. In fact, the ver- ~ical shear vibratory amplitude appears to be lowest at these 

"LINEARITY CHECK" flight condit:ons. 

31 ... ...... . ~---... "-.. -'-----.... -.: ~ 
'-1'-. 

, '. 

Although curve crossings have not been specifically mentioned 

as such, th~y appear in most of the figures which display loads analysis results. They are prominent in those figures which involve variatiors in flat ~late equivalent area for 

auxiliary thrust. Most of these :..igures which displa" loads 

indicate that, in general, loads are decreased by . fuselage/wing/engine upwash at low values of fe, but are 

increased at high values of fee 

32 

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w ex: 

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3000 

2000 

1000 

o 

"..;..'" 

ROTOR ANALYSiS: 8-65 

UPWASH PROCESSOR: B-21 

3-D POTEtdTiAl FLOW: '\-230 

ISOLATED 

ROTOR 

2 3 4 I) 6 7 8 9 10 11 12 13 14 16 18 17 18 19 20 21 22 

FLIGHT cO~mrnON 

Figure 8-1. Effact of RSRA Upwash on Calculated Rotor Po\vsr 

H 

4 26 26 27 

00 

"TI;ll3 

-oQ 

02 

0)::> ::OrC-o 

C)::> 

:PO c: fTl 

-1-

<w 

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Q 

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W 

o 

lt: 

::; 

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T 

10 

e 

4 

2 

o 

\, 

ROTOR ANALYSiS: 8-65 

UPWASH PROCESSOR: 8-21 

3-D POTENTIAL FLOW: 1\-230 

ROTORWlTH 

FUSELAGE 

UPWASH 

/ 

.......... . , ........ , .. ". 

2 3 4 5 e 7 8 9 10 11 12 13 14 Hi 16 17 18 19 20 21 22 23 24 '-!,5 26 27 

FLIGHT CONDITIDN 

Figure 8-2. Effect of RSRA Upwash on Calcuiated Equivalent lift-fa-Drag Ratia 

~ ,; 

,~ 

. 

% 

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i= 

CI) 

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.01 

o 

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f' 

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'/: 

ROTOR ANALYSIS: B-65 

UPWASH PROCESSOR: 13-21 

3-D POTENTIAL fLOW: 1\-230 

fi\' 

I'f 

ISOLATED 

ROTOR "" 

ROTORwrrH 

FUSELAGE 

UPWASH 

I 

00 

. ." ;;a 

..... "U~ 0-- 0:;; 

""'- "'" I. 

to" C):!t 

):>0 

r- rtf 

~ za 

2 3 .. 6 6 7 8 9 10 11 12 13 14 15 10 17 18 19 20 21 22 23 24 25 28 27 

FliGHT CONDITION 

Hgut:e 8-3. Effect of ASRA Upwash on the Calculated Elastic Twist Deflection at the Tip - Vibratory Component 

" 

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V 

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\ \ ~:,'>'-' 

.20 

.16 

.10 

.05 

o 

... ..... -. \ ',:,.. 

ROTOR ANALYSIS: 6-65 

UPWASH PROCESSOR: 6-21 

3-D POTENTiAL FLOW: A-230 

-'''~ 

ISOLATED 

ROTOR 

I 

I!~ 

/ 

i#" 

\ 

ROTOR WiTH 

FUSELAGE 

UP\~JASH 

2 3 4 Ii 6 7 S 9 10 11 12 13 '" 16 16 11 18 19 20 21 22 23 24 25 28 21 

fliGHT COt"OITION 

Figure 8-4. Effect of ASRA Upwash on the Calculated Fourth and Eighth Harmonics of Rotor Thrust " ' 

" 

~ 

~ ':,,, 

. 

-:;;.; 

~~:;, 

-t'4 

f; 

'.;; 

0,.1 

:~~ 

, 

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~., 

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.... 

c: 

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.25 

...... .20 

!Z 

I.IJ 

Z 

o 

0... 

:l! 

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...... w 

, . 

5 l\ 

,.) 1> 

0:: 

o 

t-$ .10 

J: 

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a 

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-< :i! .06 

0:: 

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Z 

o 

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~ 

.....• - \ 

~,' ---- ---.------. \. \ . .,. . ,~ " 

ROTOR ANALYSIS: 8-65 

UPWASH PROCESSOR: 8-21 

3-D POTENTIAL FLOW: A-230 

'\, 

.\ 

'.\ 

ISOLATED 

ROTOR ROTOR WITH 

FUSELAGE 

UPWASH 

00 

~;:;;; 

"UQ 

('\ "-

o~ ;Or-

.0-0 

c> 

:PO 

ej''.l 

~U> 

2 3 4 I) EI 1 8 9 10 11 12 i3 14 16 16 11 18 19 20 21 22 23 24 25 26 27 

FliGHT CONDrrK)N 

Figura 8-5. Effect of RSRA Upwash on the Calculated Fourth and Eighth Harmonics of Rotor Torque 

'. 

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" 

~ ~ ~, 

... 

'" 'J 

t; 

~ 

rj 

" 

~ 

" P 

I 

f, 

f, 

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I 

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10 

8 

6 

uoe 

4 

2 

"';' 

1 

WITHOUT UPWASH -

WITH UOWASH - - -

GROSS ~"EIGHT '" 26,400 LB 

ROTOR LIFT" 26,400 LB 

ROTOR RAOIUS:a 30 FT 

2 

o ~------~------~------~------~------~------~----~ 100 110 120 130 140 150 160 170 

/ FLIGHT VELOCITY - J(NOTS 

/ 

Figure 8-6. Variation of Equivalent Lift-ta-Drag Ratio With Flight Velocity 

From Loads Analysis. Rotor Lift, Gross Weight, and Rotor 

Radius Are Held Constant Numerals Nc:-:: SymbOlS Indicate 

Flight Condition. 

38 

. /;' :'''' /. I I I .\ . 

,. 

.. 

: 
I . ___ :. _______ ..:...-.---....... - ... - ..... 

j 

". ") I 

,:',~ 

I ".~! . . 'I· 

I .' ,,---.. 

! '. f 

/. 

... -~ ... ~ i 

n 

'.1 1 •• J 

.' . H 

" 

r-' 

,.' I I . 

'/ /" 

/ 

2,000 

1,800 

1,600 

1,400 

1,200 

PLL 

AMPLITUDE· 

LB 

1,000 

800 

600 

400 

WITHOUT UFWASH 

WITH UPWASH ____ _ 

GROSS WEIGHT :0 26,400 LB 

ROTOR LIFT'" 26,400 LB 

ROTOR RADIUS" 30 FT 

1 

/ 

/ 

/ 

I 

I 

/ 

I 

/ 

~ 

I 

I 

/ 

200 ------~------~------~------~------~------~----~ 100 110 120 130 140 150 

FLIGHT VELOCITY· KNOTS 

Figure B-7 Variation of Pitch Link Load Vibratory Amplitude 

With Flight Velocity From Loads Analysis. Rotor 

Lift, Gross Weight, and Rotor Radius Are Held 

Constant. Numerals Near Symbols Indicate 

Flight Condition. 

39 

160 170 

/' - .. ,., 
.. ~. ! 

! . I 

I 

I 

I 

/. to: 

.' 

i 

/ 

/' ~ 

, --\...:. 

/ / 

I 

5,000 

4,000 

3,000 

VERTICAL 

SHEAR 

AMPLITUDE· 

LB 

2,000 

1,000 

/.\. 

GROSS WEIGHT ~ 26,400 LB 

ROTOR LIFT - 26,400 LB 

ROTOR RADIUS ~ 30 FT 

WITHOUT UP\'VASH 

WITH UPWASH - - --

----if ~~'-:=~--------~25 - . 

1 

o~------~------~------~------~------~------~------- 100 110 120 130 140 150 

FLIGHT VELOCITY· KNOTS 

Figure 8-8. Variation of Flap Hinge Vertical Shear Vibratory Amplitude 

With Flight Velocity From Loads Analysis. Rotor Lift. 

Gross Weight. and Rotor Radius Are Held Constant 

Numerals Near Symbols Indicate Flight Condition. 

40 

/ 

160 170 
l 

\ ".-...., i, 

1/ 

/, 

I , , I , 

/ :' 

. { 

'I 

, I 

.i' :~, ,'! '. 

, .' 

, '., i 

! 

/ 

I 

't . , ; 

2,800 

2,400 

2,000 

1,600 

FZF· 

LBS 

1,200 

800 

400 

" . 

WITHOUT UPWASH 

WITH UPWASH ___ _ 

GROSS WEIGHT 2 26,400 LB 

ROTOR LIFT:a 26,400 LB 

ROTOR RADIUS • 30 FT 

1 

," , "/ 

. '/ 

... -----:~--~-.---------

O------~------~I~----~------~------~------~----~ 100 110 120 130 140 150 160 

FLIGHT VELOCITY· KNOTS 

Figure &9. Variation of VerticClI Hub Force Fourth Harmonic 

Amplitude With Flight Velocity From Loads Analysis. 

Rotor Lift, Gross Weight, and Rotor Radius Are 

Held Constant. Numerals Near Symbols Indicate 

Flignt Condition. 

41 

170 

"4 \,,; 
·, 

~ 

/ .'---

10 

8 

6 

LlDE 

4 

2 

WITHOUT UPWASHWITH UPWASH - --

GROSS WEIGHT = 26.400 LB 

ROTOR L1FT::I 13,333 LB 

WING LIFT" 8,067 'B 

ROTOR RADI US < :sil t:T 

G 

o 100 ------------------------*-------~------~------~----~ 110 120 130 140 150 160 

FLIGHT VELOCITY - KNOTS 

Figure 8-10, Variation of Equivalent Lift-to-Drag Ratio With Flight Velocity 

From Loads Analysis. Rotor Lift. Gro!:S Weight. Wing Lift. and 

Rotor Radius Are Held Constant. Numeral'i Near Symbols 

Indicate Flight Condition. 

42 

170 

. i 

I , 

I 

~ 4 
~ 

2,000 r1,800 

1,600 

1,400 

1,200 

PLL 

/ 

~----~--~·~~~~------.-.. -.. -.-._-.. -.~.!~_~t.-_-._-.. -.-.. -.. -.~~~ 

GROSS WEIGHT" 26,400 LB 

ROTOR LIFT" 18,333LB 

WING LiFT::o 8,057 LB 

ROTOR RADIUS" 30 FT 

WITHOUT UP"NASH ---

WITH UPWASH- - -

AMPLITUDE· 

LB 

1,000 

800 

600 

400 

0--- --- --

/' 

200 ~ ____ ~ ______ ~ ______ ~ ______ ~ _____ ~ ______ -LI ______ ~I 

100 110 120 130 140· 150 160 170 

FLIGHT VELOCITY· KNOTS ' . Figure 8-11. Variation of Pitch Link Load Vibratory Amp Etude 

With Flight Velocity From Loads Analysis. Rotor 

Lift, Gross Weight, Wing Lift, and Rotor Radius 

Are Held Constant. Numerals Near Symbcls 

hldicate F light Condition. 

43 
. "\ 

[~'ei:S'!f".v;6':~5"'C'1(j-~",,,<: S": .flO .. - .. 

J 

~ 

~ 

5,000 

4,000 

3,000 

VERTICAL 

SHEAR 

AMPLITUDE· 

LB 

2,000 

1,000 

GROSS WEIGHT = 26,400 LB 

ROTOR LIFT = 18,333 LB 

WING LIFT = 13,067 LB 

ROTOR RADJUS :: 30 FT 

0-_ 

5 

WITHOUT UPWASH --__ 

WI-;H UPWASH - - -

26 

100 150 

FLIGHT VELOCITY· KNOTS 

Figure 8·12 Variation of Flap Hinge Vertical Sh~ar Vibratory 

Amolitude With Flioht Velocity From Loads Analysis. 

Rotur Lift, Gross Weight, Wing Lift, and Rotor 

Radius Are Held Constant. Nu.,lerals Near Symbols 

IndiCClte Flight Condition . 

44 

160 

..... • .-..,'4? 

.,A 

170 
---~! 

,I 

'-

I .~. 

2,800 r 

2,400 

2,000 

1.600 

FZF· 

LBS 

1,200 

800 

400 

WITHOUT UPWASH 

WITH UPWASH ____ _ 

GROSS WEIGHT = 26,400 LB 

ROTOR LIFT = 18,333 LB 

WING LlFT:a 8,067 LB 

ROTOR RADIUS::I 30 FT 

26 

----=8 

6 

o "--__ ---i ___ --" ___ .-.. ___ --i.. ___ ..I.' ___ --i..' ----' 

100 1'0 120 130 140 150 160 

FLIGHT VELOCITY· KNOTS 

Figure 8-13. Variation of Vertical Hub Force Fourth Harmonic 

Amplitude With Flight Velocity From Loads Analysis. 

Rotor Lift, Gross Weight, Wing Lift, and Rotor 

Radius Are Held Constant. Numerals Near Symbols 

Indicate Flight Condition. 

45 

.. ---~ .... - ",~-,,,,""'!~,,,, .. ' 

./.-" ' 

.,"- - .. 

170 
/ 

.--:" 

8 

6 

LlOE 

4 

2 

GROSS WEIGHT = 18.333 LB 

ROTOR LIFT'" 18.333 LB 

FLAT PLATE AREA = 22.9 FT2 

WITHOUT UPWASH ---

WITH UPWASH - - -

8 

o~----~------~------~------~----~------~------~ 

. ! 

100 110 120 130 140 150 160 

FLIGHT VELOCITY - KNOTS 

Figure 8- 14. Variation of EqUivalent lift·ta-Drag Ratio With Flight Velocity 

From Loads Analysis. Rotor Lift. Gross Weight. and Equivalent 

Flat Plate Area Are held Constant. Numerals Near Symbols 

Indicate Flig'H Condition. 

46 

170 

I 

I' 

1· 

. ~-

/ 
"- r- , 

, 

./ 

,/ 

0-./ : 

, 

'-

\ 

. '.-

2,000 

1,800 

1,600 

1,400 

1,200 

PLL 

GROSS WEIGHT:: 18,333 LB 

ROTOR LIFT = 18,333 LB 

FLAT PLATE AREA = 22.9 FT2 

WITHOUT UPWASH ---

WITH UPWASH - - -

AMPLITUDE· 

LB 

1,000 

/ 

/' 

800 ./ 

B 

600 ~ 

400 

200 ~-----~------~'------~I------~I------~------~'------~I 100 110 120 130 140 150 160 170 

FLIGHT VELOCITY· KNOTS 

Figure 8-15. Variation of PItch Link Load Vibratory Amplitude 

With Flight VelocitY From Loads Analysis. Rotor 

Lift, Gross Weight, and Equivalent Flat P!ate Area 

Are Held Constant' Numerals Near Symbols 

Indicate Flight Condition . 

47 

>;; 

l.. , 

. -- -------.7----.------~~ . 

. , ___ jO. -... \ 

(-.-;----... L~ .. :, r. 
/ 

I 

I 

• t 

" 

. / 

--

'/ ,.i. 

I ' 

'.~-: 

. .' ~ .. 

~ 

o. r.f. il 

'0 

, I 

5,000 

4,000 

3,000 

VERTICAL 

SHEAR 

AMPLITUDE· 

LB 

2,000 

1,000 

100 

WITHOUT UPWASH ____ _ 

WITH UPWASH ___ _ 

GROSS WEIGHT" 18,333 LB 

ROTOR LIFT = 18,333 LB 

FLAT PLATE AREA = 21..9 FT2 

Q..::-~ =if". 7 ---- . 

27 

110 120 130 140 150 

FLIGHT VELOCITY· KNOTS 

Figure 8- 16. Variation of Flap Hir,ge Vertical Shear Vibratory 

Amplitude With Flight Velocity From Leads Analysis. 

Rotor Lift, Gross Weight, an::! Equivalent Flat Plate 

Area Are Constant. Numerals Near Symbols Indicate 

Flight Condition . 

./ ), ",' 

... :' ~ . 

48 

.- .. /''''-

," /' 

160 

" 

170 
.' , ./ 

.. 

--''---

/ 

.I 

" ./ 

'j 

:.j I 

I·" ./ 

. , 

2,800 

2,400 

2,000 

1,600 

FZF· 

LBS 

1,200 

800 

400 

GROSS WEIGHT'" 10,333 LB 

ROTOR LIFT:: 18,333 LB 

FLAT PLATE AREA:a 22.9 FT2 

-0 

---- 8 

WITHOUT UPWASH ---

WITH UPWASH - - -

o~----~------~----~------~------~----~------~ 

100 110 120 130 140 150 160 

FLIGHT VELOCITY· KNOTS 

Figure 8-17. Variation of Vertical Hub Force Fourth Harmonic 

Amplitude With Flight Velocitv From Loads Analysis. 

Rotor Lift, Gross Weight, and Equivalent Flat Plate 

Area Are Held Constant. Numerals Near Symbols 

Indica\e Flight Condition. 

49 

170 

, 
/. 

./~ " 

.' J '~ 

i 

I 

.~ .. -~ 

.I10 

B 

6 

L/DE 

4 

2 

0 

0 

W:THOUT UPWASH 

WITH UPWASH ____ _ 

I 

2 

FLIGHT VELOCITY = 162.5 KN 

ROTOR RADIUS = 30 FT 

I I 

4 6 B 

T COS (XshrR2 - PSF 

I 

10 12 

Figure 8-'8. Variation of Equivalent Lift-to-Drag Ratio With Disk Loading 

From Loads Analysis. Flight Velocity and Rotor Radius Are 

Held Constant. Numerals Near S'{mbols Indicate Flight 

Condition . 

50 

I 

14 

, 

1-

! \ 
_. I 

/ 

/ 

I 

.1 

/ 

... ---- , 

" .... , -' -'. 

I 

/ 

/. ... 

-'----.~ 

2.000 FLIGHT VELOCITY = 162.5 KN 

ROTOR RADIUS:: 30 FT r 

WITHOUT UPWASH I 

1.800 WITH UPWASH - - - I 

1.600 I 

I 

1.400 I 

I 2 

1.200 I 

PLL 

AMPLITUDE· I 

LB 

1.000 0-

0----d 

4 19 

800 

600 

400 

200 ______ ~ ______ ~ ______ ~ ____________ ~ __ • ____ ~J ______ ~ 

o 2 4 6 8 10 12 

T COS et/lTR2 - PSF 

Figure 8-19. Variation of Pitch Link Load Vibratory Amplitude 

With Disk Loading From Loads Analysis. Flight 

Velocity and Rotor Radius Are Held Constant. 

Numerals Near Symbols Indicate Flight Condition. 

51 

/, ., '/'!. ! , .I~· . i· 

14 

; 

, 

i 

; , 

, 

.. i 
/ 

r ,/ ~ 

---L-:.. 

./ 

;: I , 

,'['.-') 

/" / ... . .':'. 

,i' / 

.: / 

.' ' 

/ 

;/ -... /' 

.. 

. /( /1 

I 

/ ,,/ 

/' 

I 

/ 

. ,j 

Ii" 

I 

I .~, 

-:1 

I. 

I' 

./ 

5,000 

4,000 

3,000 

VERTICAL 

SHEAR 

AMPLITUDE· 

LB 

2,000 

1,000 

, . 

o 

WITHOUT UPWASH ____ _ WITH UPWASH ___ _ 

2 4 

FLIGHT VELOCITY :0 162.5 KN 

ROTOR RADIUS:o 30 FT 

19 

6 8 10 

Figure 8-20. Variation of Flap Hinge Vertical Shear Vibratory 

Amplitude With Disk Loading From Loads Analysis. 

Flight V",locity and Rotor Radius Are Held Constallt. 

Numerals Near Symbols Indicate Flight Conditioll. 

52 

'r:'- '-' / .. - I, :~:' I " /" 'j ~ 

12 

' .. - . , 

I 

14 

i 

•• 
/ 

( 

I, ' 

" j'. 

! 

, ' 

, ' 

, , , " 

I 

, ' , / 

: / 

,/ 

I 

/ 

" 

.•. / 

:/1 

:~.J!J ,'.-: ' 

.. . ,i. ; 

" , 

I ! ' ; , I 

, t: I i , /."/ 

'i .' r 

,f I .' .' 

2,800 -

2,400 

2.000 

1,600 

FZF· 

LB 

1.200 

800 

400 

FLIGHT VELOCITY:a 162.5 KN 

ROTOR RADIUS" 30 FT 

WITHOUT UPWASH ---

WITH UPWASH - - -

4 

~ "b 

2 

o~----~------~------~----~~----~------~-----~ o 2 

Figure 8-21. 

" ' 

4 6 8 10 12 

T COS ~i'rrR2 - PSF 

Variation of Vertical Hub Force Fourth Harmonic Ampliturle With 

Disk Loading From Loads Analysis. Flight Velocity and Rotor 

Radius Are Hp.ld Con:otant. Numerals Ne~r Symbols Indicate 

Flight Condition . 

53 

! 

14 

I 

· l ~ .. 
;,: 

/' 

" I .. _.l_·,c .. -

I 

,' .. ,/ I , 

/ 

. ./", / / 

, ' 

" " 

.. ~ 

i , 

... ~ 

r. 

, 

.X 

" 

I ./ 

i 

I' ,,' 

,(. 

I / / .. ' 

, /.' ,,' , j.' , / 

10 

8 4 

6 

L/OE 

4 

2 

0 

0 

20 

2 4 6 

WITHOUT UPWASH-· ---

WITH UPWASH - - - -

ROTOR LIFT::r 18,333 LB 

FLIGHT VELOCITY:2 162.5 KN 

ROTOR RAOI US" 30 FT 

-- 6 

! 

8 10 

! 

12 

LIFT - LB X 10.3 

14 

Figure 8-22. Variation of Equivalent Lift·to-Drag Ratio With Wing Lift From 

LoaC;s Analysis. Rotor Lift, Flight Velocity, and Rotor Radius Are 

Held Constant Numerals Near Symbols Indicate Flight Condition. 

54 

" 

{~ • 
, , 

:' ,'! 

/, 

, ~' 

-_.-' . 

:]. 

, . " 

I, 

, 

, ' 

: ' 

. .~"..----

',' 

~: 

I 

! 

I 

.I 

/ 

2.000 

1,800 

1,600 

1,400 

1,200 

PLL 

AMPLITUDE· 

LB 

1,000 

800 

600 

400 

' I I, 

WITHOUT UrWASH ________ _ 

WITH UPWASH __ _ 

ROTOR LIFT" 18.333 LB 

FLIGHT VELOCITY ::I 162.5 KN 

ROTOR RADIUS = ~O FT 

20 

6 

" ; . , 

200 ~----~------~----~~----~------~----~------~ 

o 

, / 

2 4 6 8 10 12 

LIFT - LB X 10- 3 

Figure 8-23. Variation of Pitch Link Load Vibratory Amplitude 

With Wing Lift From Loads Analysis. Rotor Lift. . r;light Velocity, and Rotor Radius Are Held Constant. 

Numerals Near Symbols Indicate Flight Condition. 

55 

14 

/' 
; 

I 

; 

It 

,/ r-

, 

/ 

l 

\ 

, 

i 

, 

t 

I 

I 

5,000 

4,000 

3,000 

VERTICAL 

SHEAR 

AMPLITUDE· 

LB 

2,000 

1,000 

o 

WITHOUT UPWASH 

WITH UPWASH ___ _ 

ROTOR LIFT:z 18,333LB 

FLIGHT VELOCITY..: 162.5 KN 

ROTOR RADIUS = 30 FT 

......... ........ "0- --

20 

2 4 6 8 

LIFT - LB X 10.3 

10 

Figure 8·24. Variation of Flap Hinge Vertical Shear Vibratory 

Amplitude With Wing Lift From Loads Analysis. 

Rotor Lift, Flight Velocity, and Rotor Radius Are 

Held Constant. Numerals Near Symbol!; Indicate 

Flight Condition. 

56 

: 

12 14 
/ 

r i 

--------------------~~ 

2,800 

2,400 

2,000 

WITHOUT UPWASH 

WITH UPWASH ____ _ 

ROTOR LIFT = 18,333 LB 

FLIGHT VELOCITY'" 162.5 KN 

ROTOR RADIUS'" 30 FT 

-- 20 

1,600 

FZF· -- LB 

1,20t' 

800 

400 

o 

o 2 4 6 8 10 12 

LIFT - LB X 10.3 

Figure 8-25. Variatiol; of Vertical Hub Force Fourth Harmonic Amplitude With 

Wing Lift From Loads Analysis. Rotor Lift. Flight Velocity. and 

Rotor Radius Are Held Constant. Nlur.erals Near Symbols 

Indicate Flight Condition. 

57 

, 

II 

14 
I ~ 

10 

8 

6 

LlOE 

4 

2 

.--~~'>-~~----'~~---'-.~r;~~ 

'\, .. 

WITHOUT UPWASH ----

WITH UPWASH - - ---

GROSS WEIGHT" 18,333 LB 

ROTOR ~I FT '" 1 B,333 LB 

FLIGHT VELOCITY = 162,1; KN 

ROTOR RADIUS'" 30 FT 

_ _ -0 ......... _____ --- ................ - ---0 

8 

OL-----~------~------~------~----~------~----~ o 4 8 12 16 20 24 

fo - sa FT 

Figure 8-26. Variation of Equivalent Lift·to·Drag Ratio With Flat Plate Area for 

A'Jxiliary Thru':t From Loads Analysis. Rotor Radius, Rotor Lift, 

Gross Weight, odd Flight Velocity Are Held Constant. Nu-nerals 

Near Symbols Indicate Flight C.ondition. 

58 

28 

i 

., 
'.''', , . 

-[--

-,.-

--, 

/,--

\ -, 

--", '-. '-

. 

-.. : 

---

....... ~, 

2,000 

1,800 

l,6C{) 

1,400 

1,200 

PLL 

AMPLITUDE· 

LS 

1,000 

800 

600 

400 

200 

0 

WITHOUT UPWASH ____ _ 

WITH UPWASH __ _ 

4 

GROSS WEIGHT ~ 18,3~3 LB 

ROTOR LIFT'" 18,333 LB 

FLIGHT VELOCITY" 162.5 KN 

ROTOH RADIUS" 30 FT 

----- --

I 

8 12 16 

fa- sa FT 

--

...A 

8 

I 

20 

Figure 8-27. Variation of Pitch Link Load Vibratory Ampli~ude 

With Flat Plate Area far Auxiliary Thrust From 

Loads Analysis. Rotcr Radius, Rotor Lift, Gross 

Weight, and Flight Veloc!ty Are Held Constant. 

Numerals Near Symbols Indicate Flight Canriilian. 

59 

~.--

.. 

I J 

24 28 

-.i '\ '. I .~ 
---' .. 

-

.: .-' 

-\. ,--- \~-

\ , .. \-

\ "-

"" 

\ 

\ . 

\ 

-.-~ 

/ 

.. .. 

5,000 

4,000 

3,000 

VERTICAL 

SHEAP. 

AMPLITUDE· 

LB 

2,000 

1,000 

a 

4 

WITHOUT UPWASH 

WITH UP\,VASH ___ _ 

GROSS WEIGHT'" 18,333 LB 

ROTOR LI FT = 18,333 LB 

FLIGHT VELOCITY = lG2.5 KN 

POTOR RADI US :a 30 FT 

'if 

22 

4 8 12 16 

f8-sa FT 

20 

Figure 8·28. Variation of Flap Hinge Vertic31 Shear Vibratory 

Amplitl..!de With Flat Plate Area for Auxiliary 

Thrust From Loads Analysis. Rotor Radius, Rotor 

Lift, Gross Weight, and Flight Velocity Are Held 

Constant. Numerals Near Symbols Indicate Flight 

Condition. 

" .' . -

60 

------

24 28 

" ;', \ 

--

- I 

f 
...... ~1 -', 

.. ' 

, , " \ . " , 

/ 

~'~ .... ~, ... ~ .. ,.'" ....... _ .... _--_.-- -.. ~ 

2,800 

2,400 

2,000 

1,600 

FZFLBS 

1,200 

800 

4] 

0 

4 

I 

4 

Figure 8-29. 

" 

WITHOUT UPWASH ______ _ 

WITH UPWASH ____ _ 

GROSS WEIGHT :0 18,333 LB 

ROTOR LIFT:: 18,333 LB 

FLIGHT VELOCITY" 162.5 KN 

ROTOR RADIUS'" 30 FT 

I I I I I I 

8 12 16 20 24 28 

1-0 - sa FT 

Variation of Vertical Hub Force Fourth Harmonic Amplitude With 

Flat Plate Area for Auxiliary Thrust From Loads Analysis. Rotor 

Radius, Rotor Lift, Gross Weight, and Flight Velocity Are Held 

Constant. Numerals Near Symbols Indicate Flight Condition. 

61 

\. 

>-, 

;1 

" 

" 
, .... : 1 

;-... 

,I 

" 

" , 

-, 

I , 

! , \ 

\ 

, \ 

10 

a 

6 

LICE 

4 

2 

WITHOUT UPWASHWITH UPWASH---

ROTOR L1FT:a 18,333 LB 

FLIGHT VELOCITY:or 162.5'KN 

ROTOR RACI US" 30 FT 

_ ---0-.:.-. 

-- -- 23 ~ 

10 

o ------~------~------~----~~----~------~----~ o 4 

Figure 8-30. 

8 12 16 20 24 

fe- sa FT 

Variation of Equivalent Lift·to·Drag Ratio With Flat P'late Area for 

Auxiliary Thrust From Loods Analysis. Rotor Radiu!'. Rotor Lift. 

and Flight Veiocity Are Held Constant. Numerals Near Symbols 

Indicate Flight Condition. 

62 

\:.' ! .":' 

28 

,_--t 

\-
/ / 

/ 

r 

2,000 

1,800 

1,600 

1,400 

1,200 

PLL 

AMPLITUDE· 

La 

1,000 

800 

600 

400 

WITHOUT UPWASH 

WITH UPWASH __ _ 

ROTOR LI FT· 18,333 LB 

FLIGHT VELOCITY" 162.5 I(N 

ROTOR RADIUS" 30 FT 

23 10 

200~----~------~------~----- ______ ~I------~--~ 

o 4 8 12 16 20 24 28 

fe- sa I'T 

Figure 8-31. Vc:riation of Pitch Link Load Vibratory t-mplitude 

With Flat Plate Area for AU.<iliary Thrust From 

Leads Analysis. Rotor R'idin. Rotor Lift. and 

Flight Velocity Are He,J Constant. Numerals 

Ne-lr Symbols Indicate Flight Condition. 

63 

j 

\ 

.-:" 
}--- . 

- .A~ -;--::--

, . 

~-

< 

, 

/ 

.:..--r--- / 

, 

I 

i 

... ----

5,000 

4,000 

3,000 

VERTICAL 

SHEAR 

AMPLITUDE· 

LB 

2,000 

1,000 

o 

WITHOUT UPWASH ____ _ 

4 

WITH UPWASH __ 

ROTOR LlFT::I 18,333 LB 

FLIGHT VelOCITY = 162.5 KN 

ROTOR R.ADIUS = 30 FT 

/' 

/' 

/' 

- 23 

8 12 16 

fa - sa FT 

,/' 

."fl 

/ 

10 

20 

Figure 8-32. Variation of Flap Hinge Vertical Shear Vibratory 

Amplitude With Flat Plate Area for Auxiliary 

Thrust From Loads Analysis. Rotor Radius. Rotor 

Lift, and Flight Velocity Are Held Constant. 

Numerals Near Symbols Indicate Flight Condition. 

64 

24 

.-I 

28 . , 

I 

< 
, 

/' 

/ 

.I 

I 

(~-

-- '-

2,800 

2,400 

2,000 

1,600 

6 

ROTOR LIFT = 18,333 LB 

FLIGHT VELOCITY = 162.5 KN 

ROTOR RADIUS" 30 FT 

WITHOUT UPWASH ---

WITH UPWASH - - -

FZF· 

LB 

1,200 

800 

400 

O~----~~----~------~------~------~---_--~----~I o 4 8 12 16 20 24 28 

fo - sa FT 

Figure 8-33. Variation of Vertical Hub Force Fourth Harmonic AmjJlitude 

With Flat Plate Area for Auxiliary Thrust From Loads Analysis. 

Rotor Radius, Rotor Lift, and Flight Velocity Are HelLl 

Constant. Numerals Near Symbols Indicate Flight Condition. 

65 

. I 

-/ 

~-, 
! . 

I 

; 

I 

J. .• 

/ 

..... ,-, ! 

, 

, 

\ 

" 

-,. :' ~ 

! ' 

, ': .. 

I, 

, . 

, I . , 

l 

I 

10 

I " ~ 

ROTOR LIFT:z 18,333 LB 

FLIGHT VELOCITY:z 162.5 KN 

ROTOR RADI US = 30 FT 

-----

WITHOUT UP-WASH ---

WITH UPWASH - - -

---0--_ 

8 K--------------"' . ___ --- -_ 4 23 

10 

6 

L/DE 

4 

2 

o h-________________________ ~ __________________________ ~I 

o 11.45 22.9 

o 4,033.3 8,066.7 

fa - sa FT 

LlFT- LB 

Figure 8-34. Variation of Equivalent Lift·to-Drag Ratio With Flat Plate Area for 

Auxiliary Thrust and Wing Lift From Loads Analysis. Rotor Lift. 

Flight Velocity. and Rotor Radius Are Held Constant. Numerals 

Near Symbols Indicate Flight Condition. 

66 

. ''11' 

" 
.r'" 

/' 

I ,;- ...... .... ~ I 

., 

/' 

" 'J' 

,'" 

I 

/ 

, 

.I 

" , 

1,800 

1,600 

1,400 

1,200 

PLL 

AMPLITUDE· 

LB 

1,000 

£00 

600 

400 

I " 

ROTOR LIFT:I 18,333 LB 

FLIGHT VELOCITY" 162.5 KN 

ROTOR RADIUS .. 30 FT 

WITHOUT UPWASH ---- WITH UPWASH --- -

----------- ...0 

-- "~~~--------------0 23 10 

2000~----------------------1·A-r-·----------------------'2~2.J9 1 . ..:. 

o 4,033.:) 8,066.7 

fe- sa FT 

LIFT - LB 

Figure 8-35. Variation of Pitch link Load Vibratory Amplitude 

With Flat Plate Area for Auxiliary Thrust and Wing 

Lift From Loads Analysis. Rotor Lift, Flight 

Velocity, and Rotor Radius Are Held Constant. 

Numerals Near Svmbols Indicate Flight Condition. 

67 

; . " J I" / 

,- -. -- ~ 

II< 

i 

I 

\ 
·- .~ 

, 

/' 

I 

" 

I , 

\. -' 

/ 

'iI j/---~~ 

! 

, 

• 'I 

5,000 

4,000 

3,000 

VERTICAL 

SHEAR 

AMPLITUDE· 

La 

2,000 

1,000 

o 

o 

I 

WITHOUT UPWASH ____ _ 

WITH UPWASH ___ _ 

ROTO R 1I FT = 1 B,333 LB 

FLIGHT VELOCITY = 162.5 KN 

ROTOR RADIUS = 30 FT 

23 

11.45 

4,033.3 

fo- sa FT 

LIFT - LB 

Figure 8·36. Variation of Flap Hinge Vertical Shear Vibratory 

Amplitude With Flat Plate Area for Auxiliary 

Thrust and Wing Uft From Loads Analysis. Rotor 

lift, Flight Velocity, and Rotor Radius Are Held 

Constant. Numerals Near S"mbols Indicate Flight 

Condition. 

68 

10 

22.9 

B,066.7 

.. t , . 

, 
/ 

/ 

/ 

/ 

I 

./ 

.;--

, 

i 

i 

J 

J 

I 

i 

J 

, ~ I 

/ /1. ., I '/ ' , 

~"""""~J,. .. __ ~ .. -. .... ..-,.. ....... -_. 

2,800 

2,400 

2,000 

1,600 

FZF· 4 

LB 

1,200 

800 

400 -

ROTOR LIFT::a 18,333 LB 

FLIGHT VELOCITY" 162.5 KN 

ROTOR RADIUS = 30 FT 

WITHOUT UPWASH ---

WITH UPWASH - - -

-0 

10 

o--------------------------~--------------------------- o 

o 

11.45 

4,033.3 

fa - sa FT 

LIFT - LB 

Figure 8-37. Variation at Vertical Hub Force Fourth Harmonic Amplitude With 

Flat Plate Area for Auxiliary Thrust and Wing Lift From Loads 

Analysis. Rotor Lift, Flight Velocity, and Rotor Radius Are Heir.! 

Constant. Numerals Near Symbols Indicate Flight Condition. 

69 

22.9 

8,066.7 

. 

• 

, 

j 
'/~. 

I 

! 

i 

I 

, 

I ' 

-i 

/ 

, ' 

... / 

10 

8 

6 

LlOE 

4 

2 

,/ 

WITHOUT UFWASH 

WITH UPWASH 

DISK LOAD'" 9.34 LB/FT2 

FLIGHT VELOCITY = 162.5 KN 

e--- ---&=~ 12 24 ....g 

2 

o~----~------~----~~----~------~----~------- 20 22 24 26 28 30 32 

ROTOR RADIUS - FT 

Figure 8-38. Variation of Equivalent Lift·to-Drag Ratio With Rotor Radius 

From Loads Analysis. Flight Velocity and Disk Loading Are 

Held Constant Numerals Near Symbols Indicate Flight 

Condition. 

70 

34 

1A, 

. , 

, 

\ 

t 

" 
/ 

r--

.--... ~,-:.-, 

( 

2,000 ? 

/ 

/ 

1,800 WITHOUT UPWASH WITH UPWASH _____ / 

/ 

DISK LOAD = 9.34 LB/FT2 1,600 / FLIGHT VELOCITY = 162.5 KN 

/ 

/ 

1,400 I 

;1 2 

1,200 

PLL 

AMPLITUDE· 

LB 

1,000 12 

800 

600 

400 

200 ~----~------~------~----~~----~--.----_I~------' 20 22 24 26 28 30 32 34 

ROTOR hADI US - FT 

Figure 8-39. Variation of Pitch !.ink Load Vibrator'! AmplituJe With Rotor 

Radius Front Luads Analysis. Fligh~ Velocity iird Disk Loading 

Are Held Constar.t. Numerals Near Symbols Ind:cate Flight 

Condition. 

71 

\ 

: 

, 

'. 
"'v- \ \ . \\ < " 1." ~'~---•• ---.- ...... 4' ... ~· , . P. '-'.' '. 

" ... -_._- ~ ... - ---~~.---....--..--------. \ 

.... ,,~ ~ '( ......... 't\,. \;- ..... . ." .... . 

'! .. :,t;:: "''''';~'~ \,::,," \',.", :~' __ .' . --- I ~t·~.l .. , .... ·• ;..1.." ,. ..'. '. ••• .... -

~ 

! i / I; 

! 

I 

\ 

'7~" t J 

···>1 

-..'.~ .' '--'1" 

• J: 

/. 

I :t • J .II' 

/j' 

~. .'. -' I· .' 

, 

. 

lt' 

i 

I .' 

5,000 I 

4,000 

3,000 

VERTICt'L 

SHEAR 

AMPLITUDE· 

LB 

2,000 

1,000 

WITHOUT UrWASH 

WITH UPWASt1 __ 

DISK tOAD" 9.34 LB/FT2 

FLIGHT VELOCITY = 162.5 KN 

12 

o~ ____ ~ ______ ~ ____ ~~_ 

20 22 24 26 28 30 

ROTOR RADI US - FT 

Figure 8-40. Variation of Flap Hinge Vertical :3h~or ViL,ratory 

Amplitude Wi'.:' Rotor Radius From I.oads Analysis. 

Flight Velocity and Oi~k Loading Are Held Constant. 

Numerals Near Symbols Indicate Fligh( Condition . 

72 

32 34 
,.; 

.~ 

, 

. 

- , 

-

-----

. ,. 

I· 

., 

.. 

, 

\.: ..... " . 

, 

. r-

\ 

'. ~ \. ~ i • 

\ \,. . .' 

.~' :: .------

2,800 WITHOUT UPWASH 

WITH UPWASH ___ _ 

2,400 

DISK LOAD • 9.34 LB/FT2 

FLIGHT VELOCITY:II 1132.5 KN 

2,000 

1,600 

FZF· 

LB 

1,200 

800 

400 

0 1 I -1 

20 22 24 26 28 30 32 

ROTOR RADiUS - FT 

Figure: 8-41. Variation of Vertical Hub Force Fc~:rth Harmonic Amplitude With 

Rotor Radius From L03ds Analysis. F-light Velocity and Disk 

Loading Are Held Constant. Numerals Near Symbols indicate 

Flight Condition. 

73 

. .; -~.-. . ,-- .... '\ -~ 

-

~,. . ..J 

34 

:I ", 

.. -. - -----_... -¢' . -\;;;I - - i 
,,:,~ 

..-- , 

".-' ...... 

'--":: . 

f" ... 1 

- ""\ .. ~~ 

~.'~ -.-

.:-:--~ 

-."'- -'-;-

.. -.;.--

\. 

-" .• _'" 

-;-: .. ;'-..... '" 

I'~, _ J 

9.0 CONCLUSIONS l.lID RECmmENDATIONS 

It is obvious from th~ discussion and figures in Section 8.0 

that the effects of upwash on the fuselag~, wings, and/or engines of the RSRA reflect complicated flow interactions, not 

always lending themselves to simple or straightforward interpretation. 

At any rate some generalizations can be stated. Upwash from 

the fuselage and auxiliary engines decreases the required rotor 

power and increases LIDE and the flap hinge vertical shear vibratory amplitude. The tip elastic twist deflection is most 

influenced by fuselage/wing/engine upwash at high as opposed to 

low flight velocities. Wing upwash decreases T4/To and Q./Qo. Fuselage/wing/engine upwash changes TalTo mainl¥ at high flight velocities and decreases Qs/Qo mainly at low fllght velocities. 

The PLL amplitude is increased by fuselage/wing/engine upwash. Fuselage/wing upwash increases FZF, while fuselage or fuselage/ engine upwash decreases it. 

It is recommended that follow-on work focus on the interpreta- tion of these effects. 

74 

"--' -_. ----- . " 

. I 

-. ". .-~ 

:.... 

" 

y 

" 

. I 

. ~\ ---
>""-. , 

'~- .. :\ ._----

"\ 

\

_ .. ·.,1/ ,-

, . , , 

'..i 

-'\ 

'\,~ -, ........ 

\ 

~ .. -

. \,:" -

'. 

'I" 

10.0 REFERENCES 

1. 

2. 

3. 

4. 

s. 

6. 

Rahnema, M., "Alleviation of Helicopter Fusela~e-Induced 

Rotor Unsteady Loads through Deterministic Varlation of 

the Individual Blade Pitch, II NASA CR-l66234, :vray 1981. 

Bain, L., and A. Landgrebe, "Investigation of Compound Helicopter Aerodynamic Interference Effects," USAAVLABS 

Technical Report 67-44, Nove~ber 1967. 

Saaris, G.R., and N.R. Vandevender, "TEA-230 Users's l>tanual - TEA-230 Computer Program for Solving Potential Flow 

About Arbitrary Configurations and Supporting Computer Programs, II BCAC, Docwnent No. D6-41081, Renton, Washing- ton,' November 1973. 

Sewell, R., S. Lee, and T. Fukushima, "Rotor Airlcads and 

Performance Analysis with Non-Uniform Induced Inflow.1I 

Boeing Doc. D8-0312 - Original Release December 1967. 

Tarzanin, F., and J. Ranieri, "Aeroelastil:: Rotor Analysis Program C-SO," Boeing Report D210-10371, Philadelphia, Pa. 

Revised 1978. . 

Dadone, L., IIU.S. Army Helicopter Design DCitcom, Volume I, 

Airfoils," USAAMRDL CR 76-2 (NASA CR-153247), September 1976. 

75 

'-

"-

" 0\ 

.- . 

", 

:~ . 

. \ 

~ 

Ir -.. 

" 

, : 

'\ ... .l!,~ , 

~( " 
':--..:::' 

. \.~ti 

---" 

'j 

. , 

.... 

-/\, 

I 

" 

._ .. ;./' -~ 

. -~.'. 

..... , 

\ 

. " .. ~. ... 

'-. :' 

--'--,/\ .. ,'~ .... . -'-"!.' I, .. " : 

_"'-.vi 

I 

/ 

.. .,,;', .. ,'.: 

t .... :·,.'" ....... : 

'.' 

, ':------. 

\ .' 

, ; \ 

, "\.- ,.-~ ~ 

11.0 APPENDICES 

. .... " " , ;/1, -' 

'. 

,. '-. 

':'.": 

-:\ 

; , 

·f 

.' 

( ; 

.~ 

I _ 

76 

.--< .' ,-~.:A : .... ' ;,. \j \1\ r /;\'" ~\ , /.-,..,." ") ,,' j' \ ..- \ '\' , .. ',.-"~(. - ",'- ) \ 
,~ I 

" 

:,'/ 

, 

, ' 

. ~ , , I 

. \ 

" " ' 

. .':;. 

::':z·r_' I " I 

,; . 

;' " . /'~ 

, 

, , 

'. '. f 

. ...-- i·,A 

~~:::,....: I 

". 

',' ..-,- i.'_~· 

'-'.'1 '. 

I t\ 

/, ", 

f •• -.; 

; ..... '., 

, ,<-' 

" ~', 1" .... -:-

•• 1 J 

, \ 

'\ 

. . .:....... '~. 

APPENDIX A 

Potential Flow Model Coordinates 

This appendix contains the point coordinates which define the 

fuselage, wings, engines, fuselage wake, and engine exhausts 

as they occur in the si:~ potential flow ~:Jdels used in this 

study. The point coordJnates are contained in the input data 

sets used,h¥ th~ potential flow program, ,TEA-230~ to determine 

the velocltles lnduced by the fuselage/wlngs/englnes at the 

rotor blade locations. The six input data sets, one for each 

potential flow model; are re9roduced in this appendix . 

The title in the second line of each data set identifies the 

potential flow model involved. Those models involving win9s 

will have a win9 incidence of 0° unless another incidence 15 

indicated in thlS line. 

The first lii1e of each data set contains the word "CASE." The 

ninth line contains th~ first of the sets of point coordinates. 

These coordinat~s are, in order, station, ruttline, waterline. 

They are all in inche3 and they define, for ~urposes of the 

potential flow program, the corners of quadrllaterals i~om 

which source panels are made. The product of the first tH'O 

numbers in the eigh~l line indicates the number of sets ~f 

coordinate points that follow before another line similar to 

the eighth line is encountered. The number of groups indicated 

by lines similar to the eighth line is designated by the number 

in the seventh line. The totality of point coordinates defining the corners of quadrilaterals from which source panels are 

made is followed by another worci, either "ENDIr or "MULT." Most 

data followin9 either of these words refer to vortices or reference dimenslons. 

77 

-----._-, ..... --.---.,~---------' ';- / ___ lI. .:' " 

---•. JIt' #o..-.~ •• ~: • .,.. 

','. 

I '/ 

\ " :'_. 0_-.\ 

',- .:;-! 

, 

"'.;:' 

, .'t; .... I 

:,/ .. 0# '1' 

/ 

" 'I, 

/ 

,. 
· I 

/ 

.. ~--- CASE 

,.-!.' RSP.A FUSELAGE OHLY 

J D COW.!I BOEIIIG VERTOL ORG 7440 :':7834 rvs P32-74 

GEOM 

3.0000 2l1/LO l. -l. 

SOUR 

6.0 

7.00 4.00 

36.00000 0.0 95.89999 

36.00000 0.0 95.lI9999 

36.00000 0.0 95.lI9999 

36.00000 0.0 95.89999 

36.00000 0.0 95.lI9999 

36.00000 0.0 95.lI9999 

36.00000 0.0 95.lI9999 

58.79999 0.0 110.20000 

58.79999 16.e999? 10ll.09999 

58.79999 22.50000 106.00000 

53.79999 22.~0000 ~~.20000 

58.79999 22.50000 lI6.39999 

58.79999 16.89999 82.29999 

58.79999 0.0 lI2.29999 

81. 50000 0.0 119.39999 

/ '\ lI1.50000 22.09999 116.39999 , lI1.50000 29.50000 113.00000 

/ ,. lIl.S0000 29.50000 99.00000 

'.-- lIl.SOOOO 29.50000 85.00000 (. 

/' ~"..- lIl.50000 22.09999 78.09999 ~ . 

, 81.50COO 0.0 78.il9999 j 

, ' '. 120.lI9999 0.0 147.59999 I 

/ t· 

120.8999'; 23.39999 136.70000 I 

\ 120.89999 37.79999 125.89999 ! 

I. ! 120.8'1999 37.79999 10~.00000 ! 

120.lI999~ 37.79999 90.70000 

, 

120.~9999 2l1.39999 74.79999 i 

120.l!9999 0.0 74.79999 I " 7.00 13.00 * 120.lI9999 0.0 147.59999 t· 

120.lI99H 28.39999 1:56.70000 I 

120.lI9999 37. 79999 125.lI9999 120.~9?99 37.79999 108.0C!000 t 

120.lI9999 37.79999 90.70000 

120.lI9999 21L 39999 74.79999 

120.lI9999 0.0 74.79999 

133.00000 0.0 148.89999 

1:53.00000 29.20000 14/1.39<;99 

133.00000 38.119999 129.lI9999 

133. 00000 38.119999 110.79999 

'" / 133.00000 38.lI9999 91.79~'J9 

133. 00000 29.20000 72.799;9 

1:53.00000 0.0 72.79999 / 17~.29999 12.~000~ 148.lI9999 

175.29999 29.20000 145.e9999 

175.29999 3/L69999 129.89999 

175.29999 38.89999 1l0.799~9 

175~29999 la.a9999 91.79999 

."- .----

j 

I 

I 

r-- I, 78 , 

.. 

-.. - ---. k 

) 

.~~ ' .. -~~~---... ----::~.-.. -.----------- ·-----;.~I " 

\ ~. 

, . 
___ .-. .... _ .. __ ~~ .... _ .-·~.'.· .. _.~"_"O 

~ 

~/ 

i 

, ,"-" 

-;,/ 

175.29999 29.20000 72.799')9 

175.29999 o. a 72.79999 

, /~ 209.29999 21.89999 148.89999 .~/ 209.29999 29.20000 148.89999 

209.29999 38.89?99 129.89999 

209.29999 38.89999 110.79999 

~; 

209.29999 38.89999 91.79999 

209.29999 29.20000 72.79999 .. 209.29999 0.0 72.79999 

222.29999 22.70000 148.89999 

222.29999 29.20000 148.89999 

222.29999 38.89999 129.89999 

222.29999 38.89999 110.79999 

222.~9999 38.89999 91.79999 

222.29999 29.20000 72.79999 

222.29999 0.0 72.79999 

271. 00000 22.70000 148.89999 , 271.00000 29.20000 148.89999 

271.00000 38.89999 129.8')999 

271.00000 38.89999 110.79999 

271.00000 38.89999 91.79999 

271.00000 29.20000 72.79999 

271.00000 0.0 72.79999 

300.00000 22.70000 148.89999 

300.00000 29.20000 148.89999 

300.00000 38.89999 129.89999 

300.00000 38.89999 110.79999 

300.00000 38.89999 91.79999 

300.00000 29.20000 72.79999 , 300.00000 0.0 72.79999 

376.59985 17.79999 148.89999 , ~ 

376.59935 29.20000 148.89999 

376.59985 38.89999 129.89999 

376.59985 .s8.899')9 110.79999 

376.59985 38.89999 91.79999 

376.59985 29.20000 72.79999 

376.59985 0.0 72.79999 

391.69995 15.70000 147.29999 

391.69995 28.00000 147.29999 

391.69995 37.29999 129.00000 

391.69995 37.29999 110.79999 

391.69995 37.29999 92.59999 

391.69995 28.00000 74.39999 '\". 

391.69995 0.0 74.39999 

445.69995 7.87174 143.45999 

445.69995 24.50000 143.45999 

445.69995 32.70000 127.20000 

445.699'75 32.70000 110.79999 

I 445.69995 32.70000 94.39999 

I 445.69995 24.50000 77.7999:1 I 445.69995 a . a 77.79999 

500.00000 o. a 139.59999 , .500.00000 21.00000 139.59999 I 

i 500.00000 28.00000 125.39999 . 500.00000 28.00000 110.79999 

500.CCOOO 28.00000 96.20000 

500.00000 21. 00000 81.29999 

500.00000 0.0 81.29999 

600.00000 0.0 131.00000 

600.00000 13.50000 1:1.00000 

\ .. -- . 
?"".~ 

~ . ~. 

600.00000 

/ 600.00000 

600.00000 

600.00000 

600.00000 

1000.00000 

1000.00000 

1000.00000 

1000.00000 

1000.00000 

1000.00000 

1000.00000 

7.00 

133.00:100 

133.00000 

133. 00000 

133.00000 

133. 00000 

133.00000 

]33.00000 

175.29999 

175.29999 

175.29999 

175.29999 

175.29999 

175.29999 

175.29999 

209.29999 

209.29999 , I 209.29999 

i 209.29999 

209.29999 , ' 209.29999 ., ,l.- 209.29999 

222.29999 

I 222.29999 

222.29999 

222.29999 

222.29999 

222.29999 

222.29999 

271. 00000 

271.00000 

271.00000 

271.00000 

271.00000 

271. 00000 

271.00000 .. 100.00000 

300.00000 

300.00000 

300.00000 

300.00000 

300.00000 

300.011000 

348.59985 

I .348.59985 

I 

I 348.59985 I .348.59985 

348.59985 

.,---....._.---_. 

l. './ 

18.uOOOO 120.89999 

18.00000 110.79999 

13.00000 100.39999 

13.50000 89.39999 

0.0 89.89999 

0.0 111.00000 

13.50000 131.0001)0 

18.00000 120.89999 

18.00000 110.79999 

1t.00000 100.39999 

13.50000 89.89999 

0.0 89.89999 

10.00 

0.0 148.89499 

0.0 148.89999 

0.0 148.89999 

O. ') 143.89999 

O. a 148.89999. 

0.0 148.89999 

0.0 14cL 89999 

O. a 165.89999 

8.10000 165.89999 

11. 70000 163.59999 

12.10000 161.39999 

12.10000 157.39999 

12.10000 153.7'1999 

12.10000 148.89999 

0.0 179.70000 

14.60000 179.70000 

21.09999 175.50000 

22.00000 171.59999 

:!2.00000 164.299"9 

0:0.20000 157.77999 

21.89999 143.89o;C,9 

O. a 181.29999 

19.59999 181.29999 

22.70000 181.29999 

22.70000 174.79999 

22.70000 166.39999 

22.70000 158.89999 

22.70000 148.89999 

O. a 189.20000 

19.59999 189.20000 

22.70000 189.20000 

22.70000 1[11.09999 

22.70000 17;.7000:1 

22.70000 161.39999 

22.70000 148.89999 

O. a :'93.79999 

19.59999 191.79999 

22.70000 19.3.79999 

22.70000 184.79999 

22.70000 17.3.29999 

22.70000 16.3.00000 

22.70000 148.89999 

0.0 196.39999 

16.89999 196.39999 

19.59109 1%.39999 

19.59109 186.89999 

19.59109 174.59999 

80 

f .... ..·.rl,.'C.· 

V 

, 

i 

I 

I 

i 

~ '-, , 

I 

• , 

, 

1 

I 

i 

l· 
~ 

/ 

• I· ~ 

348.59985 19.!I9109 163.59999 

348.59985 19.59109 148.89999 

376.59985 0.0 188.09999 

376.59985 15.30000 188.09999 I 

~ 

376.59985 17.79999 188.09999 

376.59985 17.79999 180.29999 

376.59985 17.79999 170.09999 

376.59985 17.79979 161.00000 

376.59985 17.79999 148.89999 

391.69995 0.0 182.89999 

391.69995 13.50000 182.89999 

391.69995 15.70000 182.89999 

391.69995 15.70000 175.79999 

391.69995 15.70000 166.50000 

.191.69995 15.70000 151L29999 

391.69995 g.70000 147.29999 

500.00000 0.0 139.59999 

I :f ' 500.00000 0.0 139.59999 , ; 500.00000 0.0 139.59999 

I 500.00000 0.0 139.59999 

I 500.00000 0.0 139.59999 

500.00aoo 0.0 139.591199 

500.00000 0.0 139.59999 

7.00 4.00 

36.00000 0.0 95.89999 

36.00000 0.0 95.89999 

36.00000 0.0 95.89999 

36.00000 0.0 95.89999 

36.00000 C.O 95.89999 

36.!l0000 0.0 95.89999 

36.00000 0.0 95.89999 

c 53.79999 0.0 82.29999 

58.79999 -16.89999 82.29999 

58.79999 -22.50000 86.39999 

58.79999 -22.50000 96.~0000 

58.79999 -22.50000 106.00000 

58.79999 -16.89999 108.09999 

58.79999 0.0 110.20000 

81.50000 0.0 78.09999 

81.50000 -22.09999 78.09999 

81.50(100 -29.50000 85.COOOO 

81. 50000 -29.50000 99.00000 

81.50000 -29.50000 113.00000 

81. 50000 -22.09999 116.39999 

81.50000 0.0 119.89999 

120.89999 0.0 74.79999 

120.t9999 -28.39999 74.79999 

1;:0 .89'199 -37.79999 90.70000 

120.89'199 -37.79999 108.00000 I 

120.89999 -37.79999 125.89999 I 

120.89999 -28.39999 136.70000 

I 120.89999 0.0 147,.59999 

7.00 13.00 

120.89999 0.0 74.79999 

120.89999 -28. H999 74.79999 

120.89999 -37.79999 90.70000 

120.8'1999 -37.79999 108.00000 

120.89999 -37.79999 125.89999 

... 120.89999 -28.39999 136.70000 

120.8999<; 0.0 147.59999 

< .. / 

• 

81 
! ' 

~I'-, 

/, 

/ I 

,I I 

I 133.00000 0.11 72.79999 

I 133.00000 -29.20000 72.79999 \/ " 

IH.OOOOU -38.89999 91.79999 / " 1H.00000 -38.89999 110.79999 

/' "" 133.00000 -38.89999 129.89999 / I I 

1 133. 00000 -29.,0000 148.89999 

133.00000 0.0 148.89999 

175.29999 o. a 72.79999 

175.29999 -29.20000 72.79999 

175.29999 -38.39999 91.79999 

175.29999 -38.89999 110.79999 

175.29999 -38.89999 129.89999 

175.29999 -29.20000 148.89999 

175.29999 -12.10000 148.89999 

209.29999 0.0 72.79999 

~?9.29999 -29.20000 i2.79999 

209.Z9999 -38.89999 91.79999 

Z09.29999 -3a.89999 110.79999 

209.29999 -3a.89999 129.89999 

209.29999 -29.20000 148.89999 

! 209.29999 -21.89999 148.89999 

222.29999 0.0 72.79999 

f' 222.29999 -29.20000 72.79999 

222.29999 -38.89999 91.79999 

'Ii 222.29999 -38.89999 110.79999 i./ ", 222.29999 -38.89999 129.57999 

222.29999 -29.20000 148.89999 

i, '?2.Z9999 -22.70000 148.89999 

-~ 211.00000 o. a 7Z. 7?~99 

"1.00000 -29.20000 72.79999 

.:./1.00000 -38.899?9 91.79999 

271. 00000 -38.89999 110.79999 

f""----" --1.00000 -30.89999 lZ9.89999 

2il.00000 -29.20000 143.89999 

271.00000 -22.70000 148.8?999 

300.00000 a . a 72.79999 

300.00000 -29.20000 72.79999 

300.00000 -38.89999 91.79999 / 300.00000 -38.89999 110.79999 / 

I 300.00000 -38.89999 129.89999 

300.00000 -29.20000 148.89999 

300.00000 -22.70000 148.89999 

--

r 

376.60010 0.0 72.79999 

376.60010 -29.20000 72.79999 , 

376.60010 -38.89999 91.79999 

376.60010 -38.89999 110.79999 

3;6.60010 -3a.89999 129.89999 

376.60010 -29.20000 148.89999 

376.60010 -17.79999 143.89999 

391.69995 a . a 74.39999 

391.69995 -28.00000 74.39999 

391.69995 -37.29999 92.59999 

391.69995 -37.Z9999 110.79999 

391.69995 -37.29999 129.00000 

391.69995 -28.00000 147.29999 

391.69995 -15.70000 147.29999 

445.69995 a . a 77.79999 

445.69995 -24.50000 77.79999 

445.69995 -32.70000 94.39999 4 l.5.6999!) -32.70000 110.79999 

! , I 
" 

i. 

"--.'. 

r--

~'~J.{~.,·x~~\\::"""':·~~: .... ~~~' .-- ~.~ .' . _' ._._ .... ~~~ L.t _ ... ';.L '.~ " •. V~~:~~,: .. ':". __ ... 

445.69995 -32./0000 

445.69995 -24.50000 

445.69995 -7.87174 

500.00000 0.0 

500.00000 -21.00000 

SOl), 00000 -28.00000 

500.00000 -28.00000 

500.00000 -13.00000 

500.00000 -21.00000 

500.00000 o . 0 

600.00000 a .0 

600.00000 -13.50000 

600.001)00 -18.00000 

600.00000 -18.00000 

600.00ililO -18.00000 

600.00000 -13.50000 

600.00000 0.0 

1000.00000 0.0 

1000.00000 -U.500'0 

1000.00000 -lS.00000 

1000.00000 -18.0001l0 

10GO.OOOOO -18.00000 

1000.00000 -13.50000 

1000.00000 o. a 

7.00 10.00 

133.00000 0.0 

133. 00000 0.0 

133.00000 0.0 

In.OOOoo o. a In. 00000 0.0 

133. 00000 O. a 133. 00000 0.0 

175.29999 -12.10000 

175.29999 -12.10000 

175.29999 -12.11'000 

175.29999 -12.10000 

175.29999 -11.70000 

175.29999 -8.10000 

175.29999 0.0 

209.29999 -21.S9999 

209.2')999 -20.20000 

209.29999 -22.001l00 

209.29999 -22.000CO 

209.29999 -21.09999 

209.29999 -14.60000 

209.2999'1 0.0 

222.29999 -22.70000 

222.29999 -22.70000 

222.29999 -22.701)00 

222.29999 -22./~000 

222.29999 -22.70000 

222.29999 -19.59999 

222.29999 0.0 

271.00000 -22.70000 

271.00000 -22.70000 271.0000~ -22.70000 

271.00000 -22.70000 

271.00000 -22.70000 

271.00000 -19.59999 

271.00000 0.0 

127.20000 

143.45999 

143.45999 

81.29999 

81.29999 

96.20000 

110.79999 

125.39999 

139.59999 

139.59991 

89.89999 

89.89999 

100.39H9 

110.79999 

120.89999 

lll.00000 

131.00000 

89.89999 

89.89999 

100.39999 

110.79999 

120.89999 

lll. 00000 

131. 00000 

141L89999 

148.89999 

14S.89999 

14S.Soj999 

148.39999 

148.899/9 

14S.89999 

14S.89'H9 

153.79999 

157.39999 

161.39999 

163.59999 

165.S9999 

165 89999 

148 ... 9999 

157.79999 

b4.29999 

171.59999 

175.50000 

179.70000 

179.70000 

148.39999 

15S.89999 

166.39919 

174.79999 

181.29999 

lS1.29999 

181.29999 

148.89999 

161. 39999 

170.70000 

181.09999 

189.200CO 

189.20000 

J.89.20000 

83 

\ / • I 

\ \ \.-1 

\ 

\ 
,. 

" ./ 

,I \ 

\ :.~. - ~ 

:: ", 

i 1'-1 : .; '\ 

I'" 

rI·. 

/ 

I j , " 

I .. '" ~. " ,

f I '. I 

..,! l \ .... .: 

"T .• ' ''''.'' , \ I 

84 , 

I 

~-j , 

, __ J'l 
'. I. 

/ 

CASE 

RSRA FUSELAGE AND WINGS 

J o COWAN AERO RESEARCH ORGH 7440 EXT 3871 

GEOM 

3. 634. 1- -1. 

SOUR / 16. . .. 7. 4 • 36. O. 95.9 

36. O. 95.9 

16. !I.O 95.9 y/ 36. 0.0 95.9 

36. 3.0 95.9 

36. 0.0 95.9 

36. 0.0 95.9 / 58.8 ~.O 110.2 , 58.8 16.9 10S.1 

58.8 22.5 106. 

58.8 22.5 96.2 

58.8 22.! 86.4 

58.8 16.9 82.3 

58.8 0.0 82.3 

81.5 0.0 119.9 

81.!i ,'-.1 116.4 

81.5 29.5 113. 

31.5 29.5 99. 

(" Ill. 5 29.5 85. 

81.5 22.1 78.1 

81.5 O. Ii 78.1 

120.9 O. 147.6 

120.9 28.4 136.7 / 120.9 37.8 125.9 

/ 120.9 :'7.8 108. / 120.9 37.8 90.7 

120.9 28.4 74.8 

120.9 O. :-4.8 

7. 6. 

120.9 O. 147.6 'c 120.9 23.4 136 7 

l;0.9 37.1: 125.9 -. ,20.9 37.S lOlL 

..... - aO.9 37.8 90.7 12~.9 28.4 74.3 

12(;.9 74.8 • 

133. 148.9 

133. ,. .2 148.9 

133. 129.9 

.33. :10.8 '.n. .. ~ ,. . .. 'I ... • " -

I . ":'" .. ; ~ 72.S ,:.~ .. 72.8 

: l"~ . ..) 12.1 148.9 I .'J. :s ~C).? 148.9 /

!;~.3 3 ~ .9 129.9 

175.3 38.9 110.8 

175.3 38.9 9l.~ 

'~ 

~~ .. , 

!. '. 

85 

,. // \ . \ '. 

/ 
\ \ ' \ ! I ' , ' . l<O>jiI , . \ ,mDt ..... ~u!J.! .. A: ,~<. .-.- ,\";, .. ,-~~'-: ..... ~. ~' ... ~ •• _ •• '. ___ .~ I ..... , __ ._._._ ..... _ 

I \ 

/~, 

Or","Q...""'lAL PAGE' 

OF POOR QUALITY 

175.3 29.2 72.8 

175.3 o . 12.8 

209.3 21.9 148.9 

209.3 21.2 148.9 

209.3 38.9 129.9 

209.3 38.9 110.8 

2'l9.3 38.9 91.8 

./ 2;:1.3 29.2 72.8 

/ 

/ 209.3 o. 72.8 

./ 222.3 22.7 148.9 ",,": 222.:i 29.2 141S, 9 

222.3 38.9 129.9 

222.3 31S. 9 . 110.a 

~22.3 38.9 91.8 .. 22.3 29.2 . 7'!.1S 

222.3 o. 7;: .8 

271. 22.7 148.9 

:!71. 29.2 148.9 

i 271. 38.9 129.9 ., I 271. 38.9 110.8 ..... : : 271. 38.9 91.3 ... :~-- ~'. 271. 29.2 72.3 

/ . \ 271. O • 72.8 

.i 'J) 6. 4. 

., 271. 22.7 1411. 9 

I 271. 29.2 148.9 ,/ 271. 38.9 129.9 . ,: 271. 38.9 110 .8 

271. 38.9 9:..8 

r- 271. 29.2 72.8 ~~O. 22.7 148.9 

:!or. 2~.2 148. Q 

~1)1I. 3!.9 129.9 

300. 38.? 110 .8 

300. 38.9 91.4 

, / 3011. 38.'1 85. 

r. 376 .6 :7.8 148.9 376.~ 2'.2 148.9 ! 

376.6 38.9 129.9 I V 376.6 33.9 110.8 

.' 376.6 38.9 91..\ 

376.6 38.9 85. ~..:. 

/' 391. 7 15.7 H7.3 

3tJ' .. 7 2a. 147.3 

3'11.7 37.3 129. 

391. 7 37.3 110.8 

391. 7 37.3 92.G 

391. 7 28 • 7: .4 ! i 

., 5. 

. , ,)91.7 15.7 147.3 H~ .7 28. 147.3 

Hl.7 37.3 129. 

39Ll 37.3 11~ .t. 

391. 7 37.3 ~,.~ 

\ 

391. 7 28. 7fl.4 

391. 7 O. 74.', 

-;,\ 445.7 7.871H5 143.46 

445.7 24.S 143.46 

445.7 32.7 12·, .2 

.'- "1 '; 445.7 32.7 110.3 

'1 

. i' . . 

,I " 

~ 

R6 ~ . 

. ~ 

i S 

( '. 

, ! . ,,- / 
:""~:~ .. ~ ; .. ~'y 

I 

, ..... 

'. 

\ 

445.7 32.7 94.4 " ,. 4(5.7 24.5 77.8 .~. 

I 445.7 O. 77.15 ;: .. -< 500. O. 1.;9.6 

500. 2l. 1.39.6 

sao. Z8. lZ5.4 

500. 28. 110 .8 "."'; 500. 28. 96.2 

500. 21. 81.3 

500. a • 81.3 

600. O. 131. 

60Q. 13.' 13l. 

600. 18. 120.9 

600. 18. 110.8 .. 600. 18. 100.4 

600. 13.5 89.9 

600. O. 89.9 

1000. O. 13l. 

1000. 13.5 1.31. 

1000. 115 • 120.9 

1000. 18. 110.15 

1000. lB. 100.4 

~" 1000. 13.5 159.9 

1000. a • 159.9 

<?::" 7. 1 O. 

~ 133. O. 148.9 

1.33. O. 148.9 

133. O. 148.9 

133. O. 148.9 ./ 133. O. 148.9 

133. O. 141L 9 .. 133. O. 148.9 .. 175.3 O. 165.9 

175.3 8.1 165.9 

175.3 11.7 163.6 

175.3 12.1 161. 4 

175.3 12.1 157.4 

li5.3 12.1 153.15 

175.3 12.1 148.9 

209.3 O. 179.7 

20

'

L3 14.6 179.7 

209.3 21.1 175.5 

209.3 22. 171.6 

"," 209.3 22. 164.3 

" 209.3 20.2 157.15 ~09.3 21.9 148.9 

222.3 O. 181.3 

222.3 19.6 181.3 

222.3 22.7 181.3 

222.3 22.7 174.8 

222.3 22.7 166.4 

222.3 22.7 158.9 

222.3 22.7 148.9 

271. O. 189.2 

271. 19.6 189.2 

271. 22.7 189.2 

271. 22.7 lSl.1 

27l. 22.7 170.7 

27l. 22.7 161.4 ... 271. 22.7 148.9 

87 ("--

- JP'l' -.... -.---. 
/' 

I 

300. 

300. 

300. 

300. 

300. 

300. 

300. 

348.6 

34S.6 

348.6 

348.6 

348.6 

348.6 

348.6 

376 .6 

376 .6 

376.6 

376.6 

376.6 

376.6 

376.6 

391. 7 

391. 7 

391. 7 

391. 7 

391. 7 

391. 7 

391. 7 

500. 

SOD. 

SOD. 

500. 

SOD. 

SOD. 

500. 

36. 

7.0 

36. 

36.0000 

36.0000 

36.0000 

36.0000 

36.0000 

58.8000 

58.8 

58.8000 

58.8000 

58.8ilOO 

58.8 

58.8000 

151. 5000 

81.5 

81.5000 

81. 5000 

81.0;000 

151.5 

81.5000 

120.'000 

12'" 9 

120.90C!0 

O. 

19.6 

22.7 

22.7 

22.7 

22.7 

22.7 

O. 

16.9 

19.5911 

19.5911 

19.5911 

19.5911 

19.5911 

O. 

15.3 

17.8 

17.8 

17 .8 

17.8 

17.8 

O. 

13.5 

15.7 

15.7 

15.7 

15.7 

IS.7 

o. 

o. 

o. 

o. 

o. 

o. 

O. 

o. 

4.0 

O. 

-0.0000 

-0.0000 

-0.0000 

-0.0000 

-0.0000 

-0.0000 

-16.9 

-22.5000 

-22.5000 

-22.5000 

-16.9 

-0.0000 

-0.0000 

-22.1 

-29.5000 

-29.5000 

-29.5000 

-22.1 

-0.0000 

-0.0000 

-211.4 

-37.21000 

193.8 

193.8 

193.8 

184.S 

173.3 

163. 

148.9 

196.4 

196.4 

196 .4 

186.9 

174.6 

163.6 

141L9 

lalLl 

188.1 

188.1 

180.3 

170.1 

161. 0 

148.9 

182.9 

182.9 

182.9 

175.8 

166.5 

1511.3 

147.3 

139 .6 

139.6 

139.6 

139.6 

139.6 

139.6 

139.6 

95.9 

95.9 

95.9000 

95.9000 

95.9000 

95.9000 

95.9000 

82.!COO 

82.3 

86.4000 

96.2000 

106.0000 

108.1 

110.2000 

78.1000 

78.1 

85.0000 

~9.COOO 

113.0000 

116.4 

1l9.9~OO 

74.8000 

74.8 

90.7000 

88 
... 

. ----

OmGINAL PAGE' 15 

OF. POOR QUALITY 

120.':1000 -37.3000 108. 

120.9000 -37.8000 125.9000 

120.9 -2!L4 136.7 

120.9000 -0.0000 147.6000 

7.0 6. 

120.9000 -0.0000 74.8000 

120.9000 -28.4000 74.8000 

120.9000 -:n .aooo 90.7000 

120.9000 -37.8000 lOa. 

120.9000 -37.'\000 125.9000 

120.9000 -28.4000 136.7000 

120.9000 -0.0000 147.6000 

133.IlOOO -0.0000 72.8000 

133.0000 -29.2000 72.8000 

133.0000 -35.9000 91.8000 

133.0000 -38.9000 110.8000 

133.0000 -3S.9000 129.9000 

133.0000 -29.2000 148.')000 

133.0000 -0.0000 148.9000 

175.3000 -0.0000 72.8000 

175.3000 -29.2000 72.8000 

175.1000 -38.9000 91.8000 

175.3000 -38.9000 110.8000 

175.3000 -33.9000 129.9000 

175.3000 -29.2000 1"8.9000 

.--- 175.3000 -12.1000 148.9000 

209.3000 -0.0000 72.8000 

209.3000 -29.2000 72.8000 

209.3000 -38.9000 91.8000 

209.3000 -38.9000 110.8000 

209.3000 -38.9000 129.9000 

209.3000 -29.2000 148.9000 

209.3000 -21.9000 148.9000 

222.3000 -0.0000 72.8000 

222.3000 -29.2000 72.8000 

222.3000 -31L 9000 91.8000 

222.3000 -38.9000 110.8000 

I 222.3000 -~8.9000 129.9000 

I. :::!2.3000 

- .. '). 2000 141L 9000 

222.3000 -22.7000 148.9000 

271. 0000 -0.0000 72.8000 

!, 271.0000 -29.2000 72.8000 

i 271. 0000 -38.9000 91.8000 

I 271. 0000 -38.9000 110.8000 

271.0000 -3a.9000 129.9000 

271.0000 -29.2000 148.9000 

27l. -22.7 148.9000 

6. 4. 

271.0000 -29.2000 72.S 

271.0000 -33.9000 91.8 

271.0000 -38.9000 110.8000 

271.0000 -38.9000 129.9000 

271. 0000 -2').2000 148.9000 

271. 0000 -22.7000 148.9000 

300. -38.9 85. 

300. -38.9 91.8 

300. '-33.9 110 .8 

I 300. -31$09 129.9 

I 300. -29.2 148.9 

1 300. -22.7 1411. 9 I i I ,\ ~. ,I 

. I 

l i . , 

~ I 

4- ~ 89 

~ ~ ~ 
---

376.6 -38.9 

376.6 -38.9 

376.6 -3tl.9 

376.6 -38.9 

376.6 -29.2 

376.6 -17.8 

391. 7 -28. 

391. 7 -37.:5 

391.7 -37.3 

391.7 -37.3 

391.7 -28. 

391.7 -15.7 

7. 5. 

391.7000 -0.0000 

391.7000 -28.0000 

391.7000 -37.3000 

391.7QOO -37.3000 

391.7000 -37.3000 

391.7000 -28.0000 

391.7000 -15.7000 

445.7000 -0.0000 

445.7000 -24.5000 

445.7000 -32.7000 

445.7000 -32.7000 

445.7000 -32.7000 

445.7000 -24.5000 

445.7000-7.871745 

500.0000 -0.0000 

500.0000 -21.0000 

500.0000 -28.0000 

500.0000 -28.0000 

500.0000 -2a.COOO 

500.0000 -21.0000 

500.0000 -0.0000 

600.0000 -0.0000 

600.0000 -13.5000 

600.0000 -18.0000 

600.0000 -18.0000 

600.0000 -18.0~00 

~OO.OOOO -13.50no 

600.0000 -0.0000 

1000.0000 -0.0000 

1000.0000 -13.5000 

1000.0000 -18.0000 

1000.0000 -18.0000 

1000.0000 -18.0000 

1000.0000 -13.5000 

1000.0000 -0.0000 

7.0 10.0 

133.0000 -0.0000 

133.0000 -o.oooa 133.0000 -0.0000 

133.0000 -0.0000 

133.0000 -0.0000 

133.0000 -0.0000 

133.0000 -O.~OOO 

175.3000 -12.1000 

175.3000 -12.1000 

175.3000 -12.1000 

175.3000 -12.1000 

... ~."''"''- .. -.-

85. 

91.8 

110.8 

1~9.9 

148.9 

148.9 

74.4 

92.6 

110.8 

129. 

147.3 

147.3 

74.4000 

74.4000 

92.6000 

110.8000 

129.0000 

147.3000 

147.3000 

77.3000 

77.3000 

94.4000 

110.8000 

127.2000 

143.4600 

143.4600 

til. 3000 

81.3000 

96.2000 

110.8000 

125.4000 

139.6000 

139.6000 

a9.9000 

89.9000 

100.4000 

110.8000 

120.9000 

131. 0000 

131. 0000 

89.9000 

89.9000 

100.4000 

110.3000 

120.90CO 

131. 0000 

131. 0000 

148.9000 

141L 9000 

148.9000 

148.9000 

148.9000 

141L 9000 

148.9000 

1411. 9000 

153.3000 

157.4!iOO 

161.4000 

90 
... 

r----

ORlGfNAl PAG~'f:;' OF: POOR QUALITY 

175.3000 -11.7000 163.6000 

175.3000 -8.1000 165.9000 

175.3000 -0.0000 165.9000 

209.3000 -21. 9000 148.9000 

209.3000 -20.2000 157.8000 

209.3000 -22.0000 164.3000 

209.3000 -22.0000 171.6000 

209.3000 -21.1000 175.5000 

209.3000 -14.6000 179.7000 

209.300f) -0.0000 179.7000 

222.3000 -22.7000 148.·)000 

222.3000 -22.7000 158.9000 

222.3000 -22.7000 166.4000 

222.3000 -22.7000 174.8000 

222.3000 -22.7000 181.3000 

222.3000 -19.6000 181.3000 

222.3000 -0.0000 181.3000 

271.0000 -22.7000 143.9000 

271. 0000 -22.7000 161.4000 

271.0000 -22.7000 170.7000 

271.0000 -22.7000 131.1000 

271. 0000 -22.7000 189.2000 

271.0000 -19.6000 139.2000 

271. 0000 -0.0000 189.2000 

300.0000 -22.7000 148.9000 

300.0000 -22.7000 163.0000 

300.0000 -22.7000 173.3000 

300.0000 -22.7000 134.8000 

300.0000 -22.7000 193.8000 ,- 300.0000 -19.6000 193.8000 

300.0000 -0.0000 193.8000 

I 348.6001 -19.5911 148.9000 I 34lL6001 -19.5911 163.6000 I 348.6001 -19.5911 174.6000 

I 343.6001 -19.5911 186.9000 \' 348.6001 -19.5911 196.4000 i 

348.6001 -16.9000 196.4000 

348.6001 -0.0000 196.4000 

376.6001 -17.8000 148.9000 

376.6001 -17.8000 161.0000 

376.6001 -17.8000 170.1000 

376.6001 -17.MOO 180.3000 

376.6001 -17 .8000 188.1000 

376.6001 -15.3000 188.1000 

376.6001 -0.0000 188.1000 

391.7000 -15.7000 147.3000 

391.7000 -15.7000 158.3000 

391. 7000 -15.7000 166.5000 

391. 7000 -15.7000 175.8000 

391.7000 -15.7000 182.9000 

391. 7000 -13.5000 182.9000 

391. 7000 -0.0000 182.9000 

500. -0.0000 139.6000 

SOD. -0.0000 139.6000 

500. -0.0000 139.6000 

500. -0.0000 139.6 

500. -0.0000 139.6 

500. -0.0000 139.6000 

500. -0.0000 139.6000 

17. 10. 

91 
391. 36 56.65 71. 07 

369.4 56.17 75.35 

347.29 55.71 79.4 

325.04 55.47 81.52 

308.31 55.55 80.88 

297.19 55.74 79.13 

28lL89 56. 76.84 

283.43 56.29 74.32 

280.98 56.64 71.21 

284.09 56.93 68.64 

289.67 56.1 67.16 

297.92 . 57.23 65.97 

308.87 57.32 65.2 

325.25 57.3 65.32 

347.14 57.06 67.44 

369.18 56.74 70.29 

391. 36 56.65 71. 07 

389.72 79.71 73.68 

368.48 79.24 77 .81 

347.11 78.8 81. 73 

325.59 78.57 83.78 

309.41 78.64 83.16 

298.65 78.83 81.47 

290.63 79.08 79.26 

285.35 79.35 76.82 

282.98 79.69 73.U 

285.99 79.97 71. 32 

291. 3a 80.13 69.9 

---- 299.36 80.26 68.74 f 309.95 80.35 67.99 

325.79 80.33 68.12 

346.96 80.1 70.17 

368.27 79.79 72.92 

389.72 79.71 73.68 

388.08 102.76 76.28 

367.57 102.31 80.28 

346.92 101.88 84.06 

326.13 101.66 86.04 

310.51 101. 73 85.44 

300.12 101.91 83.81 

292.37 102.15 81.67 

287.27 102.42 79.32 

284.9S 102.75 76.41 ' ..... ; 287.89 103.02 74.01 

293.09 103.17 72.63 

300.8 103.3 71.51 

311. 03 103.38 70.79 

326.33 103.37 70.91 

346.78 103.14 72.89 

367.36 102.84 75.55 

388.08 102.76 76.28 

386.44 125.81 78.89 

366.65 125.38 82.74 

346.73 124.97 86.39 

326.68 124.7S 88.3 

311.61 124.8, 87.72 

301.59 124.99 86.15 

294.11 125.23 84.09 

289.19 125.48 81.82 

286.98 125.8 79.01 

92 
289.79 126.06 76.69 

294.81 126.21 75.36 

302.25 126.33 74.29 

312.11 126.41 n.59 

326.87 126.4 n.71 

346.59 126.13 75.62 

366.45 125.89 78.18 

386.44 125.81 78.89 

384.8 148.87 81. 49 

365.74 148.45 85.2 

346.55 148.05 88.72 

327.23 147.34 90.56 

312.71 147.91 90. 

303.05 148.013 811.49 

295.85 l41S. 3 36 .5 

291.11 148.55 84.31 

288.98 148.85 81.61 

291.68 149.11 79.38 

296.52 149.25 78.1 

303.69 149.37 77 .06 

313.19 149.44 76.19 

327.41 149.43 76.5 

346.41 149.22 78.34 

365.54 148.94 80.81 

384.3 148.87 81.49 

383.16 171. 92 84.1 

364.82 171. 52 87.67 

('- 346.36 171.13 91. 05 

327.78 170.93 92.82 

313.81 171. 92.28 

304.52 171.16 90.82 

297.59 171.38 88.91 < 293.03 171.61 86.81 , 290.99 171.91 84.21 

293.58 172.15 82.06 

! 

298.24 172.29 80.83 

305.13 172.4 79.83 I 314.27 172.47 79.19 I 327.95 172.46 79.29 

i 346.23 172.26 81. 06 

364.63 171.99 83.44 

i 383.1t. 171. 92 84.1 .. 381. 52 194.97 86.7 

;)63.91 194.59 90.13 

346.17 194.22 93.38 

328.32 194.03 95.03 

314.91 194.09 94.56 

305.98 194.24 93.16 

299.33 194.45 91.33 

294.95 194.68 39.31 

292.99 194.96 86.81 

295.48 195.19 84.75 

299.95 195.33 83.56 

306.57 195.44 82.6 

315.35 195.51 81.1'~ 

321L 49 195.49 82.09 

346.05 195.3 83.79 

363.73 195.04 116.07 

381.52 194.97 86.7 

379.83 218.03 89.3 

J 

k. 

L. 

1-. 93 

~ - -----------

- ----...•. -.. 
..... ~ 

~ 

I 

! 

I I 

i 362.99 217.66 92.59 I 345.99 217.3 95.71 

328.87 217.12 97.34 

I 316.01 217.18 96.84 

I 307.45 217 . 33 95.5 

301.07 217.53 93.74 

296.87 217.74 91.8 

294.99 2111.02 89.41 

297.38 21lL24 87.43 

301.67 218.37 86.3 

.. - 308.01 211L 47 85.33 

316.43 213.54 84.78 

329.03 218.53 84.88 

345.87 218.34 86.51 

362.82 213.10 88.7 

379.88 2111. 03 89. :5 

378.24 241.08 91. 91 

362.07 240.72 95.06 

345.8 240.39 98.04 

329.42 240.21 99.6 

317.11 240.27 99.13 

308.92 240.41 97.84 

302.81 240.6 96.15 

298.79 240.81 94.3 

296.99 240.07 92.01 

299.28 241.28 90.12 

.'. 303.!S 241.41 39.03 

309.45 241. 5 88.15 

317.51 241.57 87.58 ~ 329.57 241.56 87.68 j 

345.69 241. 38 89.23 

361.91 241.15 91. 33 

378.24 241. 08 91.91 

376.6 264.13 94.51 

361.16 263.79 97.52 

345.61 263.47 100.37 

329.97 263.3 101.86 

318.21 263.35 101.41 

310.38 263.49 100.18 

304.55 263.68 98.57 

300.71 263.88 96.8 

298.99 264.12 94.61 

301.17 264.33 92.8 

305.09 264.44 91. 76 

310.9 264.54 90.92 

318.59 264.6 90.38 

330.11 264.59 90.47 

345.51 264.42 91. 96 

361. 264.2 93.96 

376.6 264.13 94.51 

17.0 10.0 

391.3601 -56.6500 71.0700 

369.1799 -56.7400 70.2900 

347.1399 -57.0600 67.4400 

325.2500 -57.3000 65.3200 

308.8701 -57.3200 65.2000 

297.9199 -57.2300 65.9700 

289.6699 -56.1000 67.1600 

284.0901 -56.9300 68.6400 

2aO.geoo -56.6400 71.2100 

94 

.... 

----~ r,u----- .;-. -.----~, -.-
;;;:~ 

.' .. , 

. i . , 

: ! ! 

, I 

I 

I 

I 

, 

'.' 

, .. 

I-

, 

'. 

~ " ( 

283.4299 -56.2900 

288.8899 -56.0000 

297.1899 -55.7400 

308.3101 -55.5500 

325.0400 -55.4700 

347.2900 -55.7100 

369.3999 -56.1700 

391.3601 -56.6500 

389.7200 -79.7100 

368.2700 -79.7900 

346.9600 -80.1000 

325.7900 -80.3300 309~9500 -80.3500 

299.3601 -80.2600 

291. 3799 -80.1300 

285.9900 -79.9700 

282.9800 -79.6900 

285.3501 -79.3500 

290.6299 -79.0800 

29S.6499 -78.8300 

309.4099 -78.6400 

325.5901 -78.5700 

347.1101 -78.8000 

368.41100 -79.2400 

389.7200 -79.7100 

38130 0801 "102.7600 

367.3601 -102.8400 

34(..7800 -103.1400 

326.3301 -103.3700 

311. 0300 -103.3800 

300.8000 -103.3000 

293.0901 -103.1700 

287.8899 -103.0200 

284.9800 -102.7500 

287.2700 -102.4200 

292.3701 -102.1500 

300.1201 -101.9100 

310.5100 -101.7300 

326.1299 -101.6600 

346.9199 -101.8800 

367.5701 -'02.3100 

388.0801 -.L02.76DO 

386.4399 -125.8100 

366.4500 -125.11900 

346.5901 -126.1800 

326.8701 -126.4000 

312.1101 -126.4100 

302.2500 -126.3300 

294.8101 -126.:2100 

289.7900 -126.0600 

286.9800 -1.25.8000 

289.1899 -125.4800 

294.1101 -l.25.2300 

301.5901 -124.9900 

311.6101 -124.8200 

326.6799 -124.7500 

346.7300 -124.9700 

366.6499 -125.3300 

386.4399 -125.8100 

384.8000 -148.8700 

74.3200 

76.8400 

79.1300 

80.8800 

81.5200 

79.4000 

75.3500 

71. 0700 

73.6800 

72.9200 

70.1700 

68.1200 

67.9900 

68.7400 

69.9000 

71.3200 

73.8100 

76.8200 

79.2600 

81.4700 

83.1600 

83.7800 

81. 7300 

77 .810:1 

73. ~800 

76.'30!l 

75.5500 

72.8900 

70.9100 

70.7900 

71.5100 

72.6300 

74.0100 

76.4100 

79.3200 

81.6700 

83.8100 

85.4400 

86.0400 

84.0600 

80.2800 

76.2800 

78.8900 

78.1800 

75.6200 

73.7100 

73.5900 

74.2900 

75.3600 

76.6900 

79.0100 

81.8200 

84.0900 

86.1500 

87.7200 

88.3000 

86.3900 

82.7400 

78.8900 

81.4900 

95 

omc,WAl Pit 0:: is 

OF. POOR QUAlI r '( 
\..' 

365.!J"00 -148.9400 80.8100 

346.4099 -149.2200 7Il.3400 

327.4099 -149.4300 76.5000 

313.1899 -149.(,400 76.3900 

303.6899 -149. :1700 77.0600 

296.5200 -149.2500 7lL 1000 

291. 6799 -149.1100 79.3800 

288.9800 -148.8500 81.6100 

291.1101 -148.5500 84.3100 

295.3501 -148.3000 86.5000 

303.0500 -148.0800 88.4900 

312.7100 -147.9100 90.0000 

327.2300 -147.8400 90.Sf.OO 

346.5500 -148.0500 IIll.7200 

365.7400 -148.450D 85.2000 

384.8000 -148.8700 ll1.4900 

383.1599 -171.9200 114.1000 

364.6299 -171.9900 83.4400 

346.2300 -172.2600 81.0600 

3?7.9500 -172.4600 79.2900 

3"14.2700 -172.4700 79.1900 

305, I, "9 -172.4000 79.8300 

29b. ,'- ,il -172.2900 SO.8300 293.:o~al -172.1500 82.0600 

290.9900 -171.9100 84.2100 

293.0300 -171.6100 86.8100 

297.5901 -171. 3300 88.9100 

304.5200 -171.1600 90.8200 

313.&101 -171. oooe 92.2300 { 3Z7.7300 -170.9300 92.8200 

346.3601 -171.1300 91.0500 

364.&201 -171. 5200 &7.6700 

383.1599 -171.9200 84.1000 

381.5200 -194.9700 86.7000 

363.7300 -195.0400 86.0700 

346.0500 -195.3000 83.7900 

323.4<;00 -195.4900 52.0900 

315.3501 -195.5100 131. 9800 

306.5701 -195.4400 82.6000 

299.9500 -195.331'0 83.5600 

295.4800 -195.1900 84.7500 

292.9900 -194.9600 86.8100 

294.9500 -194.6&00 89.3100 

299.3301 -194.4500 91. 3300 

305.9800 -194.2400 93.1600 

314.9099 -194.0900 94.5600 

328.3201 -194.0300 95.0800 

346.1699 -194.2200 93.3800 

363.9099 -194.5900 90.1300 

381. 5200 -194.9700 86.7000 

379.8799 -218.0300 89.3000 

362.8201 -218.1000 as.7000 

.' 345.8701 -218.3400 86.5100 

" 329.0300 -2la.5300 84.8800 

316.4299 -218.5 .. 00 84.7800 

30lL 0100 -211L4700 85.3800 

301.6699 -218.3700 86.3000 

297.3799 -211LZ400 87.4300 

294.9900 -2111.0200 89.41CO 296.~701 -217.7400 91.8000 

/ 

96 

-
·1 

Q; 

.~----

OmGINJl.l Pl\G""'~ OF. POOR QUA'~,;~ 

301. u701 -217.5300 93.7400 

307.4500 -217.3300 95.5000 

316.0100 -217.1800 96.8400 

328.8701 -217 .1200 97.3400 

345.9900 -217.3000 95.7100 

362.9900 -217.6600 92.5900 

379.8799 -218.0300 89.3000 

378.2400 -241.0S00 91. 9100 

361. 9099 -241.1500 91. 3300 

345.6899 -241. 3800 89.2300 

329.5701 -241.5600 87.6800 

317.5100 -241.5700 87.5800 

309.4500 -241.5000 88.1500 

303.3799 -241.4100 89.0300 

299.2800 -241.2800 90.1200 

296.9900 -240.0700 92.0100 

298.7900 -240.8100 94.3000 

302.8101 -240.6000 96.1500 

308.9199 -240.4100 97.8400 

317.1101 -240.2700 99.1300 

329.4199 -240.2100 99.6000 

345.8000 -240.3900 98.0400 

362.0701 -240.7200 95.0600 

378.2400 -241.0800 91.9100 

376.6001 -264.1299 94.5100 

361.0000 -264.2000 93.9600 

345.5100 -264.4199 91. 9600 

330.1101 -264.5901 90.4700 

313.5901 -264.6001 90.3~00 

{ 310.8999 -264.5400 9Q.9200 

305.0901 -264.4399 91.7600 

I 301.1699 -264.!301 92.8000 

298.9900 -264.1201 94.6100 I 300.7100 -263.8799 96.8000 ! 

, 304.5500 -263.6799 98.5700 

310.3799 -263.4900 100.1800 

318.2100 -263.3501 101.4100 

329.9700 -263.3000 101.8600 

345.6101 -263.4700 100.3700 

361.1599 -263.7900 97.5200 

376.61J11l -264.1299 94.5100 

8. 2. t" 271. O. 72.8 • 2M.09 O • 68.64 

289.67 O. 67.16 

297.92 O. 65.97 

308.87 O. 65.2 

325.25 O. 65 .. 32 

347.14 O. 67.44 

391. 7 O. 74.4 

271. 29.2 72.8 

284.09 29.2 68.64 

289.67 29.2 67.16 

297.92 29.2 65'.97 

308.87 29.2 65.2 

325.25 29.2 65.32 

347.14 29.2 67.44 

391. 7 28. 74.4 

8.0 2.0 

391. 7 -0.0000 74.4 

t 97 

-1:'J 

/ 
- , 

347.J.J99 -0.0000 67.4400 

325.2500 -0.0000 65.3Z00 

308.8701 -0.0000 65.200!l 

297.9199 -O.OOCO 65.9700 

289.6699 -0.0000 67.1600 

284.0901 -0.0000 68.6400 

271. 0000 -0.0000 72.eooO 

391. 7 -211. 74.4 

347.1399 -29.2000 67.4400 

325.2500 -29.2000 65.3200 

308.8701 -29.2000 65.2000 

297.9199 -29.2000 65.9700 

289.6699 -29.20otJ 67.1600 

284.0901 -29.2000 68.6400 

271. 0000 -29.2000 72.8000 

17. 2. 

391. 7 26. 74.4 

376.6 38.9 85. 

347.29 38.9 85. 

325.04 3lL9 85. 

308.31 38.9 85. 

300. 38.9 85. 

289. 35.22069 80.37241 

282. 32.879.H 77.42759 

271. 29.2 72.8 

284.09 29.2 68.64 

289.67 29.2 67.16 

297.92 29.2 65.97 

3OlL87 29.2 65.2 

325.25 29.2 65.32 ~, 347.14 29.2 67.44 , 369.18 ~8.6061t6 70.88251 I 391. 7 28. 74.4 

391. 36 56.65 71. 07 ,J 369.4 56.17 75.35 

H7.29 55.71 79.4 

325.04 55.47 81.52 

308.31 55.55 80.38 

297.19 55.74 79.13 

288.89 56. 76.84 

'283.43 56.29 74.3, 

280.98 56.6t- 71. :!1 

284.09 56.9:> 68.64 

-, 289.67 56.1 67.16 

297.92 57.23 65.97 

308.87 57.32 65.2 

325.25 57.3 65.32 

347.14 57.06 67.4.4 

369.18 56.74 70.29 

391. 36 56.65 71. 07 

17.0 2.0 

391.7000 -28.CooO H.4000 

369.1799 -28.6065 7.D.8325 

347.1399 -29.2Doo 67.4400 

325.2500 -29.2000 65.3200 

308.8701 -29.2000 65.2000 

297.9199 -2 .... 2000 65.9700 

289.6699 -29.2000 67.1600 

284.0901 -29.2000 63.6400 

271.0000 -29.2000 72.1::000 

98 

.... 

------
O~IC&!j~J': r-:.\f.;~'.~.::: 

OF POO~ QU;.~lT'I 

21!2.UUOO -32.8793 77. 4~76 

289.0000 -35.2207 80.3724 

300.0000 -3~.9000 85.0000 

308.:5101 -38.9000 85.0000 

325.0400 -38.9000 85.0000 ~47 .HOO -38.9000 85.0000 

376.6001 -38.'1000 85.0000 

391. 7000 -28.0000 74.4000 

391.3601 -56.6500 71.0700 

369.1799 -56.7400 70.2900 

347.1399 -57.0600 67.4{,00 

325.2500 -57.3000 65.3200 

308.8701 -57.3200 65.2000 

297.9199 -57.2300 65.9700 

2t9.6699 -56.1000 S7.1600 

284.09ill -56.9300 68.6400 

280.980Q -56.6400 71.2100 

2t:3.4299 -56.2900 74.3200 288.889~ -5b.0000 76.&400 

297.1899 -55.7400 79.1300 

308.3101 -55.5500 ~O.8800 

325.0400 -55.4700 81 5200 

347.2900 -55.7100 79.4000 

369.3999 -56.1700 75.3500 

391. 3601 -56.6500 71.0700 

MULT 

2. 

11. 9. 7. 1. Ill. O. 

285.35 79.63 74.34 

{ 290.63 n.59 74.63 

298.65 79.54 75.16 

309.41 79.49 75.6 

325.59 79.45 75.95 

347.11 79.45 75.96 

368.48 79.52 74.37 

389.72 n.71 73.68 I 411.29 79.71 71. 98 I 

I 454.51 79.71 69.72 

I 

91)00. 79.71 -165.62 

287.27 102.69 76.92 

292.37 10:::.65 77 .25 i 300.12 102.6 77.71 , 

! 

. 310.51 102.55 78.13 

::;26.13 102.51 78.48 

34£'.92 10Z.51 71L49 

367.57 102.53 77.92 

388.08 102.76 76.23 

408.92 10Z.76 74.64 

450.66 10Z.76 72.46 

9000. 102.76 -162 .. 88 

289.19 lZ5.74. 79.5 

294.11 1~ 5.71 79.82 

301.59 125.60 80.26 

311. 61 lZ!).61 80.67 

326.68 1Z5.57 81. . 346.73 125.57 81. 01 

366.65 125.64 80.46 

386.44 125.81 78.89 

4D6.54 125 .• 11 77. ~1 

446.81 125.81 75.2 

99 

., 
":.,": 

" 

, 

-,- .,.--

- :" { 

;.1 

" 

' .. '. " ',.-:-

" 

" ,", 

. ' ~ " 

' .. : 

'. 

~/ .. _---

I 

\ .' \ 

\ 

. \ 

, 

9000. 125.81 -160.15 

291.11 148.3 82.08 

295.85 148.77 82.39 

303.05 148.72 82.82 

312.71 148.67 83.21 

327.23 148.64 83.53 

346.55 148.64 83.54 

365.74 148.7 83.01 

384.8 148.87 81. 49 

404.17 148.87 79.97 

442.96 148.87 77.94 

9000. 148.t7 -157.41 

293.03 171.86 84.67 

297.59 171.82 84.96 

304.52 171. 78 85.~1 

313.81 171.73 85.75 

327.18 171. 7 86. 06 

346.36 171. 7 86.07 

:!64.82 171.76 85.56 

383.16 171.92 84.1 

401. 79 171. 92 82.63 

439.11 171. 92 80.68 

9000. 171.92 -154.67 

294.95 194.91 87.25 

299.33 194.811 87.53 

3C5.98 194.84 87.93 

314.91 194.79 88.29 

328.32 194. n 88.58 

346.17 194.76 88.59 

363.91 194.82 88.1 

381.52 194.97 t6.7 

399.41 194.97 85.29 

435.26 194.97 83.41 

91100. 194.97 -151.93 

296.87 217.97 89.83 

301.07 217.94 90.1 

307.45 217.89 90.48 

316.01 217.'5 90.83 

328.87 217.<12 91.11 

345.99 217.82 91.12 

362.99 217.87 90.65 

379.88 218.03 8';' 3 

397.04 2IlL03 :37.95 

431.41 218.03 86.15 

9COO. 218.03 -149.1" 

298.79 241. 02 92.41 

302.151 240.99 92.67 

308.92 240.95 93.03 

317.11 240.92 93.37 

329.42 240.119 93.64 

345.8 240.88 93.64 

362.07 240.93 93.2 

378.24 241.08 9l. 91 

394.66 241.08 90.62 

427.56 241.1'8 88.89 

9000. 241.08 -146.45 

300.51 261.77 94.73 

304.37 261. 75 94.9~ 

310.24 261. 71 95.33 

318.1 261. 67 95.65 

100 
329.91 261.64 95.91 

345.63 261.64 95.92 

361. 25 261. 69 95.49 

376.76 261.83 94.25 

392.52 261.83 93.01 

424.1 261.133 91.36 

9000. 261.83 -143.98 

.050192 .085453 .120618 .172921 .242C18 .219928 

.10887 

388.93 91.17 74.97 .07889 -.11: 36 .99119 

387.29 114.22 77.58 .07889 -.le 36 .99119 

385.64 137.27 80.18 .07889 -.1: 36 .9?119 

384. 160.32 82.78 .07889 -.le 36 .99119 

3&2.36 183.37 85.39 .07889 -.1: 36 .99119 

380.72 206.42 87.99 .07889 -.10: 36 .99119 

379.08 229.47 90.59 .07889 -.1: 36 .99119 

377 .44 252.52 93.2 .07889 -.1: 36 .99119 

11. 9. 7. 1. 10. O. 

285.35 -79.63 74.34 

290.63 -79.59 74.68 

298.65 -79.54 75.16 

309.41 -79.49 75.6 

325.59 -79.45 75.95 

"..-- 347.11 -79.45 75.96 

368.48 -79.52 74.37 

389.72 -79.71 73.68 

411.29 -79.71 71.98 

454.51 -79.71 61.72 

9000. -79.71 -165.62 

2&7.27 -102.69 76.92 

2'i2.37 -102.65 77.25 

I 300.12 -102.6 1'7.71 

I' 310.51 -102.55 78.13 . 326.13 -102.51 78.48 

346.92 -102.51 78.49 

367.57 -102.58 77.92 

388.08 -102.76 76.28 

408. ?2 -102.76 74.64 

I 450.66 -102. n 72.46 

9000. -102.76 -162.88 I 

, 289.19 -125.74 79.5 ~ 294.11 -125.71 79.112 

301. 59 -125.66 80.26 

311.61 -125.61 80.67 

326.68 -125.57 81. 

346.73 -1~5.57 81. 01 

366.65 -125.64 80.46 

386.44 -125.81 78.89 

406.54 -125.81 77 .31 

446.81 -125.81 75.2 

9000. -125.1H -16Q.15 

291.11 -148.8 82.08 

295.85 -14a.~7 112.39 

303.05 -148 2 82.82 

312.71 -141S,67 83.Zl 

327.23 -144.64 83.53 

346.55 -141!.64 83.54 

365.74 -148.7 83.01 

384.8 -148.87 81.49 

404.17 -148.87 79.97 

/-~ 

1 

~ 101 ~ 
,,~-

t 

"-' 

I 

. 

442.96 

9000. 

293.03 

297.59 

304.52 

313.:11 

327.78 

346.36 

364.G2 

383.16 

401. 79 

439.11 

9000. 

294.95 

299.33 

305.98 

314.91 

328.32 

346.17 

363.91 

3t1.S2 

399.41 

435.26 

9000. 

296.87 

301. 07 

307.45 

316.01 

328.87 

345.99 

362.99 

379.88 

397.04 

431.41 

9000. 

298.79 

302.81 

308.92 

317.11 

329.42 

345.8 

362.07 

378.24 

394.66 

427.56 

9000. 

300.51 

304.37 

310.24 

318.1 

329.91 

345.63 

361.25 

376.76 

392.52 

424.1 

9000. 

.050192 

.10887 

388.93 

-148.87 

-148.87 

-171.86 

-171.82 

-171. 78 

-171.73 

-171.7 

-171. 7 

-171.76 

-171. 92 

-171. 92 

-171. 92 

-171.92 

-194.91 

-194.88 

-194.84 

-194.79 

-194.76 

-194.76 

-194.82 

-U4.97 

-194.97 

-194.97 

-194.97 

-217 . 97 

-217.94 

-217.89 

-217 .85 

-217.82 

-217.82 

-217.87 

-218.03 

-218.03 

-218.03 

-218.03 

-241. D2 

-240.99 

-240.95 

-240.92 

-240.89 

-240.88 

-240.93 

-7.41.08 

-241.08 

-241.08 

-241.08 

-261. 77 

-261. 75 

-261. 71 

-21>1.67 

-261. 64 

-261.64 

-261.69 

-Z/i 1. 83 

-261.83 

-261.83 

-261.83 

.085453 

-91.17 

77.94 

-157.41 

84.67 

8( •. 96 

85.37 

85.75 

86. 06 

86.07 

85.56 

/34.1 

82.63 

80.68 

-154.67 

87.25 

87.53 

87.93 

88.29 

88.58 

8!LS9 

88.1 

86.7 

85.29 

83.41 

-151. 93 

89.83 

90.1 

90.48 

90.83 

91.11 

91.12 

90.65 

89.3 

37.95 

C6.15 

-149.19 

92.41 

92.67 

93.03 

93.37 

93.64 

93.64 

93.2 

91. 91 

90.62 

88.89 

-146.45 

94.73 

94.98 

95.33 

95.65 

95.91 

95.92 

95.49 

94.25 

q:S.Ol 

91.36 

-143.98 

.120618 .172921 .242&'18 .219928 

74.97 .07889 .10636 .99119 

102 
387.29 -114.22 77 .58 .07889 .10636 .99119 

385.64 -137.27 M.ts .07889 .10636 .99119 

334. -160.32 82.78 .078&9 .10636 .99119 

382.36 -183.37 85.39 .07889 .10636 .99119 

330.72 -206.42 87.99 .07889 .10636 .99119 

379.08 -229.47 90.59 .07389 .10636 .99119 

377 .44 -252.52 93.2 .07889 .10636 .99119 

B-MU 

2. 

11. 3. 7. 1. 10. Q. 

283.43 o. 71.76 

288.89 o. 72.11 

297.19 o. 72.6 

308.31 o. 73.06 

325.04 O. 1'5.42 

34;0.29 O. 73.43 

369.4 O. 76. 

392.0323 o. 77.65445 

413.67 o. 100. 

458.36 o. 120. 

9000. o. -115.3426 

283.43 56.58 71.76 

;, 288.89 56.54 72.11 

297.19 56.48 72.6 

r 30lL31 56.43 73.06 

325.04 56.39 73.42 

347.29 56.39 73.43 

369.4 56.46 72.&2 

391. 36 56.65 iL 07 

413.67 56.65 69.32 

453.36 56.65 66.93 

9000. 56.65 -168.36 

21:5.35 H.63 74.34 

290.63 79.59 74.68 

298.65 79.54 75.16 

309.41 79.49 75.6 

325.59 79.4!. 75.95 

347.11 79.45 75.96 

368.48 79.52 75.37 

389.72 79.71 73.68 

411. 29 79.71 71.98 

454.51 79.71 69.72 

9000. 79.71 -165.62 

.0501'12 .085453 .120618 .172921 .242018 .219928 i 

I .10n87 

I 390.57 68.12 72.37 .07889 -.10636 .99119 

I 11. 3. 7. l- 10. O. 

283.43 O. 71. 76 

288.89 o. 72.11 

297 .19 O. 72.6 I 308. :31 O. 73.06 

! 325.04 O. 73.42 i 347.29 O. 73.4,3 

I 369.4 O. 76. 

392.0323 O. 77.65445 

413.67 O. 100. 

458.36 O. 120. 

i 9000. O. -115.3426 

I 283.43 -56.!i8 71. 76 

, 2&8.&9 -56.54 72.11 

~i 

i 103 
". 

297.19 -56.48 72.6 

308.31 -56.43 73.06 

325.04 -56.39 73.42 

347.29 -56.H 73.43 

369.4 -56.46 72.82 

391.36 -56.65 71. 07 . , 413.67 -56.65 69.32 

458.36 -56.65 66.98 

/ 9000. -56.65 -168.36 

285.35 -79.63 74.34 

290.63 -79.59 74.68 

298.65 -79.54 75.16 

309.41 -79.49 75.6 

325.59 -79.45 75.95 

347.11 -79.45 75.96 

368.43 -79.52 75.37 

389.7Z -79.71 73.68 

411.29 -79.71 71.98 

454.51 -79.71 69.72 

9000. -79.71 -165.62 

.050192 .085453 .120618 .172921 .2~Z018 .219928 

.10M7 ,.-- . 390.57 -68.12 72.37 .07889 .10636 .99119 

\:UD 

AERO 

5. O. o. 

FORe 

307.5 a. 75.52 52112. 98.1 531.2 a. 

EHD 

~ 

, 

~ / 

104 
r 

~ ....... 

/ 

/ 

/ 

1-

.. 

CASE 

OR!~~(\~.:;.:~ Phry~ :~~ 

Of, IJocr~ Q\JALI'('lJ 

RSRA FUSELAGE AND ENGINES 

J D COWAN BOEIHG VERTOL ORG 7440 'X7a34 

GEOI1 

3.00000 400. 1. -1. 

SOUR 

S.O 

7.00 4.00 

36.00000 0.0 95.89999 

36.00000 0.0 95.89999 

36.00000 0.0 95.89999 

36.00000 0.0 95.89999 

36.00000 0.0 95.89999 

36.00000 0.0 95.S9999 

36.00000 0.0 95.89999 

58.79999 0.0 110.20000 

51l.79999 16.89999 108.09999 

58.79999 22.50000 106.00000 

58.79999 22.50000 96.20000 

58.79999 22.50000 86.39999 

58.79999 16.89999 82.29999 

58.79999 0.0 82.29999 

In.50000 0.0 119.89999 

81. 50000 22.09999 116.39999 

81. 50000 29.50000 111.00000 

81. 50000 29.50000 99.00000 

81. 50000 29.50000 85.00000 

81.50000 22.09999 78.09999 

31.50000 0.0 78.09999 

120.89999 0.0 147.59999 

120.89999 28.39999 136.70000 

120.89999 37.79999 125.89999 

120.89999 37.79999 10!L 00000 

120.89999 37.79999 90.70000 

120.89999 2!L 39999 74.79999 

120.89999 0.0 74.79999 

7.00 13. 00 

120.89999 0.0 147.59999 

120.89999 28.39999 136.70000 

120.89999 37.79999 125.89999 

120.89999 37.79999 108.00000 

120'.89999 37.79999 90.70000 

120.89999 28.39999 74.79999 

120.89999 0.0 74.79999 

133.00000 0.0 148.89999 

133.00000 29.20000 148.89999 

133.00000 38.89999 129.89999 

133.00000 3a.a9999 110.79999 

133. 00000 38.89999 91. 79999 

133.00000 2'Li:OOOO n.79??9 

133.00000 0.0 72.79999 

175.29999 12.10000 14!1.89999 

175.29999 29.200:10 148.89999 

175.29999 38.89999 129.89999 

175.29999 :58.89999 110.79999 

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105 

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209.29999 21.89999 148.89999 

209.29999 29.20000 148.89999 

209.29999 38.S9999 129.89999 

209.29999 38.89999 110.79999 

209.29999 38.899'19 91. 79999 

209.29999 29.20000 72.79999 

209.29999 0.0 72.79999 

222.29999 22.70000 148.89999 

222.29999 29.20000 148.89999 

222.29999 31L89999 129.89999 

222.29999 38.89999 110.79999 

222.29999 38.8999? 91. 79999 

222.29999 29.20000 72.79999 

222.29999 0.0 72.79999 

271.00000 22.70000 148.89999 

271. 00000 29.20000 148.89999 , 271.00000 38.89999 129.89199 /' 271.00000 38.89999 110.79999 ,/ 271.00000 38.89999 91.79999 / 

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271.00000 29.20000 72.79999 

271. 00000 0.0 72.799B 

300.00000 22.70000 lft8.89999 

300.00000 29.20000 148.89999 

300.00000 38.89999 129.89999 

( 300.00000 38.89999 110.79999 

300.00000 311.89999 91.79999 

300.00000 29.20000 72.79999 

300.00000 0.0 72.79999 

376.59985 17.79999 148.89999 

376.59985 29.20000 141L89999 

376.59985 38.89999 129.89999 

376.59985 38.89999 110.79999 

376.59985 38.89999 91.79999 

376.59985 29.20000 72.79999 

376.59985 0.0 72.79999 

391.69995 1'·.70(100 147.29999 

391.69995 28.00000 147.29999 

391. 6 9995 37.29999 129.00000 

391.69995 37.29999 110.79999 

391.69995 37.29999 92.59999 

391.69995 28.00000 74.39999 

391.69995 0.0 74.39999 

445.69995 7.a7174 143.45999 ~ ......... 445.69995 24.50000 143.45999 

-- 445.69995 32.70000 127.20000 

445.69995 32.70000 110.79999 

445.69995 32.70000 94.39999 

; 445.69995 24.50000 77.79999 

-. 445.69995 (1.0 77.79999 

500.00000 o. a 139.59999 

500.00000 21. 00000 139.59999 5DO.0000~ 23.00000 125.39999 

500.00000 2ll.00000 110.79999 

500.00000 2rL 00000 96.20000 

500.00000 21.00000 81.29999 

500.00000 n.o 81.29999 

600.00000 C.O 131.00000 

600.00000 13.50000 131.00000 

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600.00000 18.00000 110.79919 

600.00000 18.00000 100.39999 

600.00000 13.50000 89.89999 

600.00000 0.0 89.89999 

1000.00000 0.0 131.00000 

1000.00000 13.50000 131.00000 

1000.00000 18.00000 120.89999 

1000.00000 111.00000 110.79999 

1000.00000 18.00000 100.39999 

1000.00000 13.50000 89.89999 

1000.00000 0.0 89.89999 

7.00 10.00 

133.00000 0.0 148.89999 

133.00000 0.0 148.89999 

133.00000 0.0 14S.119999 

133.00000 0.0 148.89999 

133.00000 0.0 1411.89999 

133.00000 0.0 1411.89999 133.0000~ O. a 148.89999 

175.Z9999 0.0 165.89999 

175.29999 8.10000 165.89999 

175.29999 11. 70000 163.59999 

175.29999 12.10000 161.39999 

175.29999 lZ.10000 157.39999 

175.29999 12.10000 153.79999 

175.29999 lZ.10000 148.89999 

209.29999 0.0 179.70000 

209.Z9999 14.60000 179.70000 

209.29999 21. 09999 175.50000 

209.29999 22.00000 171.59999 

209.Z9999 22.00000 164.29999 

209.29999 20.20000 157.79999 

209.29999 21.89999 141LII9999 

222.29999 0.0 181.29999 

222.29999 19.59999 181.29999 

222.29999 22.70000 181.29999 

222.29999 22.70000 174.79999 

222.29999 2Z.70000 166.39999 

227..29999 22.70000 158.89999 

22Z.29999 ZZ.70000 148.8999~ 

271.00000 0.0 189.Z0COO 

271.00000 19.59999 1119.Z0000 

271.00000 22.70000 189.20000 

271.00000 2Z.70000 131.09999 

27l.00000 22.70000 170.70000 

271.00000 Z2.70000 161.39999 

271. 00000 22.70000 148.89999 

300.00000 0.0 193.79999 

300.00COO 19.59999 193.79999 

300.00000 22.70000 193.79999 

300.00000 22.70000 184.79999 

300.00000 22.70000 173.29999 

300.00000 22.70000 163.00000 

300.00000 22.70000 148.89999 

348.59985 0.0 196.39999 

348.599155 16.89999 196.39999 

348.59985 19.59109 196.39999 

348.59985 19.59109 186.89999 

348.599&5 19.59109 174.59999 

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348.59985 19.59109 1(,3.59999 

348.59985 19.59109 148.89999 

376.59985 o • a 188.09999 

376.59985 15.30000 188.09999 

376.59985 17.79999 1138.09999 

376.59985 17.79999 180.29999 

376.59985 17.79999 170.09999 

376.59985 17.79999 161.00000 

376.59985 17.19999 148.89999 

391.69995 0.0 182.89999 

391.69995 13.50000 182.89999 

391. 69995 15.70000 182.89999 

391.69995 15.70000 175.79999 

391.69995 15.70000 166.50000 

391.69995 15.70000 158.29999 

" 391.69995 15.iOOOO 147.29999 

500.00000 0.0 139.59999 

500.00000 0.0 139.59999 

500.00000 0.0 139.59999 

500.00000 0.0 139.59999 

500.00000 0.0 139.59999 

500.00000 0.0 139.59999 

500.00000 0.0 139.59999 

7.00 4.00 

36.00000 0.0 95.89999 

36.00000 0.0 95.89999 

36.00000 0.0 95.89999 

36.00000 0.0 95.89999 

36.00000 0.0 95.89999 

36.00000 0.0 95.89999 

36.00000 0.0 95.89999 

58.79999 0.0 82.29999 

58.79999 -16.89999 82.29999 

58.79999 -22.50000 86.39999 

58.79999 -22.50000 96.20000 

58.79999 -22.50000 106.00000 

58.79999 -16.89999 108.09999 

58.79999 0.0 110.20000 

. ...- 81.50000 0.0 78.09999 

" 81. 50QQO -22.09999 73.09999 .' 81.50000 -29.50000 85.00000 

.... 81.50000 -2?50000 99.00000 " 81.50000 -29.50000 113.00000 

81.50000 -22.09999 116.39999 

I 81.50000 0.0 119.89999 

120.89999 0.0 74.79999 

120.89999 -28.39999 74.79999 

120.89999 -37.79999 90.70000 

120.89999 -37.79999 108.00000 

120.899'39 -37.79999 125.89999 

--'.--- 120.89999 -28.39999 136.70000 

120.89999 0.0 147.59999 

7.0u 13.00 

120.89999 0.0 74.79999 

120.89999 -28.39999 74.79999 

120.89999 -37.79999 90.70000 

120.89999 -37.79999 108.00000 

120.89999 -37.79999 125.89999 

120.89999 -28.39999 136.70000 

120.89999 0.0 147.59999 

108 
..... 

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133.00000 0.0 

133.00000 -29.20000 

133.00000 -38.t9999 

133.00000 -38.89999 

133.00000 -38.t9999 

133.00000 -29.20000 

133.00000 0.0 

175.29999 0.0 

175.29999 -29.20000 

175.29999 -38.89999 

175.29999 -33.89999 

175.29999 -38.8?999 

175.29999 -29.20~00 

175.29999 -12.10000 

209.29999 0.0 209.29Q~9 -29.20000 

209.29999 -38.89999 

209.29999 -38.89999 

209.29999 -38.89999 

209.,9999 -29.20000 

209.29999 -21.89999 

222.29999 0.0 

222.29999 -29.20000 

222.29999 -38.89999 

222.29999 -38.89999 

222.29999 -38.89999 

222.29999 -29.20000 

222.29999 -22.70000 

271. 00000 0.0 

271.00000 -29.20000 

271.00000 -38.89999 

271.00000 -38.39999 

271.00000 -38.89999 

271.00000 -29.20000 

271.00000 -22.70000 

3oo.000ilO 0.0 

300.00000 -29.20000 

300.00000 -38.89999 

300.00000 -3F.89999 

300.00000 -38.89999 

300.00000 -29.20000 

300.00000 -22.70000 

376.60010 0.0 

376.60010 -29.20000 

376.60010 -38.89999 

376.60010 -38.89999 

376.60010 -38.89999 

376.6GQ10 -29.20000 376.6001~ -17.79999 

391.69995 0.0 

391.69995 -2t.00000 

391.69995 -37.29999 

391.69995 -37.29999 

391.69995 -37.29999 

391.69995 -23.00000 

391.69995 -1~.70000 

445.69995 "..0 

445.69995 -24.50000 

445.69995 -3~.70000 

445.69995 -37..70000 

72.79999 

72.79999 

91. 79999 

110.79999 

129.89999 

148.89999 

148.89999 

72.79999 

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91. 79999 

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148.89999 

72.79999 

72.79999 

91.79999 

110.79999 

129.89999 

148.89999 

148.89999 

72.79999 

72.79999 

91.79999 

110.79999 

129.89999 

148.89999 

148.89999 

72.79999 

72.79999 

91.79999 

110.79999 

129.89999 

141L89999 

148.89999 

72.79999 

72.79999 

91.79999 

110.79999 

129.89999 

148.89999 

148.89999 

74.39999 

74.39999 

92.59999 

110.79999 

129.00000 

147.29999 

147.29999 

77.79999 

77.79999 

94.39999 

110.79999 

109 

ORlmNAL ~;"'f~~"!3 

OF POOR QUALITY 

.. 0 
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... ' 

445.69995 -32.70000 

445.69995 -24.50000 

445.69995 -7.87174 

500.00000 0.0 

500.00000 -21.00000 

500.00000 -28.00000 

500.00000 -28.00000 

500.00000 -28.00000 

500.00000 -21.00000 

500.00000 0.0 

600.00000 0.0 

600.00000 -13.500aO 

600.00000 -18.00000 

600.00000 -18.00000 

600.00000 -18.00000 

600.00000 -13.50000 

600.00000 0.0 

1000.0000:1 0.0 

1000.00000 -13.50000 

1000.00000 -13.00000 

1000.00000 -18.00000 

1000.00000 -18.00000 

1000.00000 -13.50000 

1000.00000 0.0 

7.00 10.00 

133.00000 0.0 

133.00000 0.0 

133.00000 0.0 

133.00000 0.0 

133.00000 0.0 

133.00000 0.0 

133.00000 0.0 

175.29999 -12.10000 

175.29999 -12.10000 

175.29999 -12.10000 

175.29999 -12.10000 

175.29999 -11.70000 

175.29999 -8.10000 

175.29999 0.0 

209.29999 -21.89999 

209.29999 -20.20000 

209.29999 -22.00000 

209.29999 -22.00000 

209.29999 -21.09999 

209.29999 -14.60000 

209.29999 0.0 

222.29999 -22.70000 

222.29999 -22.70000 

222.29999 -22.ioooo 

222.29999 -22.70000 

222.29999 -22.70000 

222.29999 -19.59999 

222.29999 0.0 

271.000aO -22.70000 

271.00000 -22.70000 

271.00000 -22.70000 

271.00000 -22.70000 

271.00000 -22.70000 

271.00000 -19.59999 

271. 00000 0.0 

127.2COOO 

143.45999 

143.45999 

81.29999 

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96.20000 

110.79999 

125.39999 

139.59999 

139.59999 

89.t9999 

89.89999 

lCO.39999 

110.79999 

120.89999 

131.00000 

131. 00000 

89.89999 

89.89999 

100.39999 

110.79999 

120.89999 

131. 00000 

131. 00000 

148.89999 

148.89999 

148.&9999 

148.89999 

148.89999 

148.89999 

148.89999 

148.89999 

153.79999 

157.39999 

161.39999 

16:S.59999 

165.89999 

165.89999 

148.89999 

157.79999 

164.29999 

171.59999 

175.50000 

179.70000 

179.70000 

148.89999 

158.89999 

166.39999 

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181. 29999 

181.29999 

148.89999 

161.3999'1 

170.70000 

181.09999 

189.20000 

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300.00000 

300.00000 

300.00000 

300.00000 

300.00000 

300.00000 

300.00000 

348.60010 

348.60010 

348.60010 

348.60010 

348.60010 

348.60010 

348.60010 

376.60010 

376.60010 

376.60010 

376.60010 

376.60010 

376.60010 

376.60010 

391.69995 

391.69995 

391.69995 

391.69995 

391.69995 

391. 69995 

391.69995 

500.00000 

500.00000 

500.00000 

500.00000 

500.00000 

SoO.ooOOO 

500.00000 

9. 

175.6 

175.6 

175.6 

175.6 

17S.6 

175.6 

175.6 

175.6 

175.6 

211. 9 

211.5 

210.4 

20'.3 

208.9 

209.3 

210.4 

211.S 

211. 9 

225.9 

225.3 

224.0 

222.8 

222.2 

222.8 

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0.0 

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-19.59109 

-19.59109 

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-16.89999 

0.0 

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-17.79999 

-17.79999 

-17.79999 

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-15.70000 

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0.0 

0.0 

0.0 

0.0 

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0.0 

0.0 

0.0 

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79.9 

79.9 

79.9 

79.9 

79.9 

79.9 

79.9 

79.9 

79.9 

79.9 

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51$.6 

64.8 

79.9 

95.0 

101.2 

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79.9 

79.9 

61.9 

54.4 

61.9 

79.9 

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148.89999 

163.00000 

173.29999 

184.79999 

193.79999 

193.79999 

193.79999 

148.09999 

163.59999 

174.59999 

186.89999 

196.39999 

196.39999 

196.39999 

148.89999 

161.00000 

170.0?999 

180.29999 

188.09999 

181L 09999 

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147.299\'9 

158.29999 

166.50000 

175.79999 

1112.1I9999 

182.89999 

132.89999 

139.59999 

139.59999 

139.59999 

139.59999 

139.S9999 

139.S9199 

139.59999 

120.3 

120.3 

120.3 

120.3 

120.3 

120.3 

120.3 

120.3 

120.3 

101. 5 

107.7 

122.8 

137.8 

144.0 

137.8 

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107.7 

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98.3 

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123.7 

141. 7 

149.2 

141. 7 

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OF POOi~ QU;~L1T'1, 

111 
, 

224.0 105.4 123.7 

225.3 97.9 105.7 

225.9 79.9 98.3 

248.4 79.9 99.4 

247.9 61.5 107.0 

246.6 53.9 125.3 

245.3 61.5 143.7 

244.7 79.9 151. 3 

245.3 98.3 143.7 

246.6 105.9 125.3 

247.9 98.3 107.0 

241L4 79.9 99.4 

267.1 ·79.9 ID2.-l 

266.6 62.6 109.5 

265.3 55.5 126.7 

264.1 62.6 143.9 

263.6 79.9 151. 0 

264.1 97.2 143.9 

265.3 104.3 126.7 

266.6 97.2 109.5 

267.1 79.9 10~.4 

/ 299.3 79.9 1114.7 

'. 291L8 62.6 111.8 

297.6 55.5 129.0 

296.3 62.6 146.2 

295.8 79.9 153.3 

296.3 9:'.2 146.2 

297.6 104.3 129.0 

..- 298.8 97.2 111.8 I 299.3 79.9 104.7 I 700.7 79.9 133.4 

700.2 62.6 140.6 

699.0 55.5 157.8 

697.7 62.6 175.0 

697.2 i9.9 IS2.1 

697.7 1)7.2 175.0 

699.0 104.3 157.& 

700.2 97.2 140.6 

700.7 79.9 133.4 

1000. 79.9 133.4 

100u. 62.6 14 J.6 

1000. 55.5 ·157.8 

1000. 62.6 175.0 

1000. 79.9 182.1 

100;). 'i7.2 175.0 

1000. 104.3 157.8 

1000. 97.2 140.6 

1000. 79.9 133.4 

9. 8. 

175.60 -79.90 120.30 

175.60 -79.90 120.30 

175.60 -79.90 120.30 

I 175.60 -79.90 120.30 

175.60 -79.90 120.30 

175.60 -79.90 120.30 

175.60 -79.90 120.30 , 

I 175.60 -79.90 120.30 

175.60 -79.90 120.30 ! 

I 211.90 -79.90 101.50 

j 211.50 -95.00 107.70 

I 

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210.40 -lC1.20 122.80 

209.30 -95.00 137.80 

208.90 -79.90 144.00 

209.30 -64.80 137.80 

:?10.40 -5!.60 122.80 

211.50 -64.80 107.70 

211.90 -79.90 101. 50 

225.90 -79.90 98.30 

225.30 -97.90 105.70 

224.00 -105.·40 123.70 

:-'22 to -97.90 141.70 

222.20 -79.90 149.20 

222.30 -61. 90 141.711 

224.00 -54.40 123.70 

225.30 -61. 90 11.5.70 

225.90 -79.90 911. 30 

24l'.40 -79.90 99.40 

247.90 -98.~0 107.00 

246.60 -105.90 125.30 

245.30 -98.30 143.70 

i. ' 244.70 -79.90 151.30 

245.30 -61. 50 143.70 .. 246.60 -53.90 125.30 

247.90 -61. 50 107.00 

2411.40 -79.90 99.40 

267.10 -79.90 102.40 

266.60 -97.20 109.50 ,,--. 265.30 -104.30 126.70 , 

, 264.10 -97.20 143.90 

263.60 -79.90 151.00 

264.10 -62.60 143.90 

265.30 -55.50 126.70 

266.60 -62.60 109.50 

267.10 -79.90 102.40 

299.30 -79.90 1Il4.70 

2911.80 -97.20 111.80 

297.60 -104.30 129.00 

296.30 -97.20 146.20 

295.80 -79.90 153.30 

296.30 -62.60 146.20 

297.60 -55.50 129.00 

298.80 -62.60 111.0(' 299.30 -79.90 104.70 

700.70 -79.90 133.40 

700.20 -97.20 140.~0 

699.00 -104.311 157.110 

697.70 -97.20 175.00 

697.20 -79.90 182.10 

697.70 -62.60 175.00 

699.00 -55.';0 157.80 

700.20 -62.60 140.60 

700.70 -79.90 133.40 

1000.00 -79.90 133.40 

1000.00 -97.20 140.60 

1000.00 -104.30 lS7.80 

1000.00 -97.20 175.00 

1000.00 -79.90 1112.10 , 1000.00 -62.60 175.00 

f 1000.00 -55.50 157.80 

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END 98.1 531.2 o. 

114 
-

.~ 

( 

CASE 

omGrNr~L P.C'.S:':'· ,:.:. 

OF POOR QUAL-ITY 

RSRA FUSELAGE. WIHGS AHD ENGINES 

J 0 COWAIt AERO RESEARCH ORGH 7440 EXT 71134 

GEOM 

3. 746. 1. -1. 

SOUR 

18. 

7. 4. 

36. O. 95.9 

36. O. 95.9 

36. 0.0 95.9 

36. 0.0 9S.9 

36. 0.0 9S.9 

36. 0.0 9S.9 

36. 0.0 95.9 

S8.5 0.0 110.2 

58.8 16.9 lOlL 1 

58.8 22.5 106. 

58.8 22.5 96.2 

55.8 22.5 86.4 

58.8 16.') 82.3 

SILlS 0.0 82.3 

IS 1. 5 0.0 119.9 

In.5 22.1 116. ,. In.5 29.5 113. 

81.5 29.5 99. 

81.5 29.5 85. 

81.5 22.1 78.1 

81.5 0.0 71Ll 

120.9 O. 147.6 

120.9 21S.4 136.7 

120.9 37.3 125.9 

120.9 37.8 108. 

120.9 37.8 90.7 

120.9 2S.4 74.8 

120.9 O. 74. IS 

7. 6. 

120.9 O. 147.6 

120.9 28.4 136.7 

120.9 37.8 125.9 

120.9 37.8 108. 

120.9 37.8 90.7 

120.9 28.4 14.8 

120.9 O. 74.S 

133. O. 14S.9 

133. 29.2 IltlL9 

133. 31l.9 129.'1 

133. 33.9 110.8 

133. 3/1.9 91.8 

133. 29.2 n.s 

133. O. 72.8 

175.3 12.1 148.9 

175.3 29.2 148.9 

175.3 38.9 129.9 

175.3 38.9 110.8 

175.3 38.9 91.8 

115 
p;t'. 

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, 

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... 

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~ -

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175.3 

209.3 

209.3 

209.3 

209.3 

209.3 

209.3 

209.3 

22l.3 

222.l 

222.l 

222.3 

222.l 

222.l 

222.3 

271. 

271. 

271. 

271. 

271. 

271. 

271. 

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271. 

271. 

271. 

271. 

271. 

271. 

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300. 

300. 

300. 

300. 

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376.6 

376.6 

376.6 

376.6 

376.6 .~ 376.6 

391.7 

" 391.7 

391. 7 

". 391.7 ". 391. 7 

391. 7 

7. 

391. 7 

391. 7 

391. 7 

391. 7 

391.7 

391. 7 

391.7 

445.7 

445.7 

445.7 

445.7 

29.2 72.8 

O. 72.8 

21. 9 148.9 

29.2 148.9 

38.9 129.9 

38.9 110.8 

38.9 91.8 

29.2 72.11 

O. 72.11 

22.7 148.9 

21.2 148.9 

311.9 129.9 

31L9 110.8 

31:.9 91.8 

29.2 72.8 

O. 72.8 

22.7 148.9 

29.2 )48.9 

311.9 129.9 

3lL 9 llO .11 

38.9 91.8 

29.2 72.8 

O. 72.S 

4. 

22.7 1411.9 

29.2 148.9 

.38.9 129.9 

38.9 110.8 

38. :: 91.8 

29.2 72.8 

22.7 148.9 

29.2 148.9 

38.9 129.9 

311.9 110.8 

38.9 91.8 

38.9 85. 

17.8 148.9 

29.2 148.9 

38.9 129.9 

38.9 110.8 

3d.9 91.8 

38.9 85. 

15.7 147.l 

25. 147.3 

37.3 129. 

37.3 11Q .8 

37.3 92.6 

28. 74.4 

S. 

15.7 147.l 

28. 147.3 

37.3 129. 

37.3 110.8 

37.3 92.6 

28. 74.4 

O. 74.4 

7.871745 143.46 

24.5 143.46 

32.7 127.2 

32.7 11Q.8 

116 
445.7 

445.7 

445.7 

500. 

500. 

500. 

500. 

500. 

500. 

500. 

600. 

600. 

600. 

600. 

600. 

600. 

. 1 600. 

" 1000. ~ .... 1000. / 1000. 

1000. 

1000. 

1000. 

1000. 

7. 

r 133. 

133. 

i 13l. 

133. 

133. 

133. 

133. 

175.l 

175.3 

175.3 

175.3 

175.3 

175.3 

175.3 

209.3 

209.3 

209.3 

t, 209.3 

209.3 

209.3 

209.3 

222.3 

222.3 

222.l 

222.3 

222.3 

222.3 

222.3 

271. 

271. 

271. 

271. 

271. 

271. 

! 271. 

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; 

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24.S 

O. 

O. 

21. 

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2S. 

21. 

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13.5 

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18. 

13.5 

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18. 

18. 

13.5 

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10. 

o. 

O. 

O. 

O. 

O. 

O. 

O. 

O. 

8.1 

11.7 

12.1 

12.1 

12.1 

12.1 

O. 

14.6 

21.1 

22. 

22. 

20.2 

21.9 

O. 

19.6 

22.7 

22.7 

22.7 

22.7 

22.7 

O. 

19.E. 

22.7 

22.7 

22.7 

22.7 

22.7 

/ 

/ 

94.4 

77 .8 

77.8 

139.6 

139.6 

125.4 

110.a 

96.2 

81.3 

81.3 

131. 

Ill. 

120.9 

110.8 

100.4 

89. ~ 

89.9 

131. 

Ill. 

120.9 

110.8 

100.4 

a9.9 

89.9 

148.' 

148.9 

148.9 

14CS.9 

148.9 

148.9 

148.9 

165.9 

165.9 

163.6 

161.4 

157.4 

153.8 

148.9 

179.7 

179.7 

175.5 

171.6 

164.l 

157.8 

148.9 

181. 3 

181. l 

181. 3 

174.8 

166.4 

158.9 

14/S, 9 

189.2 

189.2 

189.2 

181.1 

170.7 

161.4 

148.9 

117 
300. O. 193.3 " ," 300. 19.6 193.8 --'--- 300. 22.7 193.3 

300. 22.7 184.3 

300. 22.7 173.3 

300. 22.7 163. 

300. 22.7 148.9 

348.6 O. 196.4 

348.6 16.9 196.4 

348.6 19.5911 196.4 

348.6 19.5911 186.9 

348.6 19.5911 174.6 

348.6 19.5911 163.6 

348.6 19.5911 148.9 

376.6 O. 1&8.1 

376.6 15.3 188.1 

376.6 17.8 188.1 

376.6 17.8 180.3 

--- 376.6 17.8 170.1 

376.6 17.8 161. 0 

376.6 17.8 148.9 

391. 7 O. 182.9 

391. 7 13.5 182.9 

391. 7 1S.7 182.9 

391. 7 15.7 175.8 

391. 7 15.7 166.5 

--- .': .. :. ..... 391. 7 15.7 158.3 

I 391. 7 15.7 147.3 

500. O. 139.6 

500. O. 139.6 

500. O. 139.6 

500. O. 139.6 

500. O. 139.6 

500. O. 139.6 SO~. O. 139.6 

7.0 4.0 

36. O. 95,9 

36. O. 95.9 

36.0000 -0.0000 95.9000 

36.0000 -0.0000 95.9000 

36.0000 -0. DODD 95.9000 

36.0000 -0.0000 95.9000 

36.0000 -0.0000 95.9000 " , 58.8000 -0.0000 82.3000 

58.8 -16.9 82.3 

58.8000 -22.5000 116.4000 

51L8000 -2Z.5000 9(,,2000 

58.8000 -22.5000 106.0000 

58.8 -16.9 108.1 

51L8000 -0.0000 110.2000 

81.5000 -0.0000 73.1000 .' 81.5 -22.1 78.1 

81.5000 -29.5000 85.0000 

81.5000 -29.5000 99.0000 

81. 5000 -29.5000 113.0000 

81.5 -22.1 116.4 

81.5000 -0.0000 119.9000 

120.9000 -0.0000 74.8000 

120.9 -28.4 74.3 

120.9000 -37.8000 90.7000 

118 
·. 

120.9000 -37.8000 lOlL 

120.9000 -37.8000 125.9000 

120.9 -28.4 136.7 

120.9000 -0.0000 147.6000 

7.0 6. 

120.9000 -0.0000 74.8000 

120.9000 -28.4000 74.8000 

120.9000 -37.8000 90.7000 

120.9000 -37.8000 lOll. 

120.9000 -37.S000 125.9000 

120.9000 -211.4000 136.7000 

120.9000 -0.0000 147.6000 

133.0000 -0.0000 72.8000 

133.0000 -29.2000 72.8000 

133.0000 -31s' 9000 91.8000 

133.0000 -311. 9000 110.8000 

133.0000 -31L 9000 129.9000 

133.0000 -29.2000 148.9000 '. 133. DODD -0.0000 148.9000 / 175.3000 -0.0000 72.8000 

175.3000 -29.2000 72.8000 

175.3000 -38.9000 91.8000 

175.3000 -311. 9000 110.8000 

175.3000 -311. 9000 129.9000 

175.3000 -29.2000 148.9000 

175.3000 -12.1000 148.9000 

--' 209.3000 -0.0000 72.8000 

( 209.3000 -29.2000 72.8000 

209.3000 -38.9000 91.8000 

209.3000 -38.9000 110.8000 

209.3000 -38.9000 129.9000 

I 

209.3000 -29.2000 1411. 9000 

209.3000 -21. 9000 148.9000 

222.3000 -0.0000 72.8000 

222.3000 -29.2000 72.8000 I' .-;-:-.... 222.3000 -38.9000 91.8000 

I 222.3000 -38.9000 110.8000 

i 222.3000 -3!L 9000 129.9000 

222.3000 -29.2000 148.9000 

I· 222.3000 -22.7000 141L 9000 

271.0000 -0.0000 72.8000 I: 271. 0000 -29.2000 72.8000 

271.0000 -38.9000 91.8000 I' ", 271. 0000 -38.9000 110 .SOOO ...... \\ 271.0000 -38.9000 129.9000 

271.0000 -29.2000 148.9000 

271. -22.7 141L 9000 

6. 4. 

271. 0000 -29.2000 n.s 

271. 0000 -38.9000 91.8 

271. 0000 -3!L 90GO 110.8000 

271. 0000 -38.9000 129.9000 

271. 0000 -29.2000 148.9000 

271. 0000 -22.7000 1411. 9000 

l 300. -38.9 ~5. 

I 300. -38.9 91.8 

300. -31>'9 110.8 

300. -38.9 129.9 

300. -29.2 148.9 

! 300. -22.7 148.9 

i 

, 

i 

,_..i.. 

~ J: . 

~ ~I 

, . ;.:. ~ 

f k~: ~ 119 I 

~., " 

I 

I&. 

- -.-._-----.. . . ! . ~~ . 
./ 

! 

, I 

.. 

./ 

/ 

-. /./' // 

.---

/ 

376.6 -38.9 

376.6 -38.9 

376.6 -38.9 

376.6 -3~.9 

376.6 -29.2 

376.6 -17.S 

391.7 -28. 

391.7 -37.3 

391.7 -37.3 

391.7 -37.3 

391.7 -28. 

391.7 -15.7 

7. S. 

391.7000 -0.0000 

391.7000 -28.0000 

391.7000 -37.3000 391.700~ -37.3000 

391.7000 -37.3000 

391.7000 -28.0000 

391.7000 -15.7000 

445.7000 -0.0000 

445.7000 -24.5000 

445.7000 -32.7000 

445.7000 -32.7000 

445.7000 -32.7000 

445.7000 -24.5000 

445.7000-7.&71745 

500.0000 -0.0000 

500.0000 -21.0000 

500.0000 -23.0000 

500.0000 -28.0000 

500.0aco -28.0000 

500.0000 -21.0000 

500.0000 -~.oooo 

600.0000 -0.0000 

600.0000 -13.5000 

600.0000 -18.0000 

600.0000 -13.0000 

600.0000 -10.0000 

600.0000 -13.5000 

600.0000 -0.0000 

1000.0000 -0.0000 

1000.0000 -13.5000 

1000.0000 -lS.0000 

1000.0000 -18.0000 

1000.0000 -18.0000 

1000.0000 -13.5000 

1000.0000 -0.0000 

7.0 10.0 

133.0000 -~.oooo 

133.0000 -0.0000 

133.0000 -0.0000 

133.0000 -0.0000 

133.0000 -0.0000 

133.0000 -a.oooo 133.0000 -0.0000 

175.3000 -12.1000 

175.3000 -12.1000 

175.3000 -12.1000 

175.3000 -12.1000 

85. 

91.8 

110.8 

129.9 

148.9 

148.9 

74.4 

92.6 

llO .8 

129. 

147.3 

147.3 

14.4000 

74.4000 

92.6000 

110.8000 

129.0000 

147.3000 

147.3000 

77.8000 

77.8000 

94.4000 

110.8000 

127.2000 

143.4600 

143.4600 

81.3000 

81. 3000 

96.2000 

110.8000 

125.4000 

139.6000 

139.6000 

89.9000 

89.9000 

100.4000 

110.8000 

120.9000 

131.0000 

131.0000 

89.9000 

89.9000 

100.4000 

110.8000 

120.9000 

131.0000 

131.0000 

148.9000 

143.9000 

148.90011 

148.9000 

148.9000 

148.9000 

148.9000 

143.9000 

153.8000 

157.4000 

161.4000 

\ 

\ 

/ \ 

120 
\ 

/ 

,r-", 

/' ORI<f.NAl PI\G£ 'IS /' 

OF poon QUAlrfY / 

175.~000 -11.7000 163.6000 

175.3000 -8.1000 165.9000 

175.3000 -0.0000 165.9000 

209.3000 -21. 9000 148.9000 

209.3000 -20.2000 157.8000 

209.3000 -22.0000 164.3000 

2119.3000 -22.0000 171.6000 

,/ 209.3000 -21.1000 175.5000 

209.3000 -14.6000 179.7000 " , 209.3000 -0.0000 179.7000 

222.3000 -22.7000 148.9000 

222.3000 -22.7000 158.9000 

..... #- ; ~ 222:.3000 -22.7000 166.4000 

222.3000 -22.7000 174.8000 ..--. 222.300D -22.7000 181. 3000 

222.3000 -19.6000 Inl. 3000 

222.3000 -0.0000 181. 3000 !,- 271. 0000 -22.7000 144.9000 

271. 0000 -22.7000 161.4000 

271. 0000 -22.7000 170.7000 

271.0000 -22.7000 llH .1000 

271. OOCO -22.7000 1~9.2000 

271.0000 -19.6000 189.2000 

271. 0000 -0.0000 189.2000 ,,-: 

, 300.0000 -22.7000 145.9000 

I 300.0000 -22.7000 163.0000 

300.0000 -22.7000 173.3000 

300.')1100 -22.7000 184.8000 

300.0000 -22.7000 In.SOOO 

300.0000 -19.6000 1n.nooo 

300.0000 -0.0000 193.GOOO 

341L 6001 -19.5911 141L 9000 

348.6001 -19.5911 163.6000 

348.6001 -19.5911 174.6000 

345.6001 -19.5911 186.9000 

348.6001 -19.5911 19!>.4000 

I 348.6001 -16.9000 196.4000 

I 348.6001 -0.11000 196.4000 

376.6001 -17.8000 148.9000 

" 376.6001 -17.8000 1H.OOOO !, 376.6001 -17.8000 170.1000 

376.6001 -17.8000 180.3000 

376.6001 -17.8000 1S8.1000 

376.6001 -15.3000 18~.1000 

376.6001 -0.0000 188.1000 

391. 7000 -15.7000 147.3000 

391. 7000 -15.7000 158.3000 

391. 7000 -15.7000 166.5000 

391. 7000 -15.7000 17S.tOOO 

391. 7000 -15.7000 182.9000 

391.7000 -13.5000 182.9000 

391. 7000 -0.0000 1112.9000 

500. -0.0000 IH.6000 

500. -0.0000 139.6000 

500. -0.0000 139.6000 

/' 500. -0.0000 139.6 

sao. -0.0000 139 .6 

500. -0.0000 139.6000 

500. -0.0000 139.6000 

17. 10. 

,""":" 

I 

I .", ..... , ~ ! I 

~, ' ".-/ -j ·~t~ 121 : ; 
122 

I 

, 

, 
ORIGlNAL pr\G'~'ls 

OF POOR QUALITY 

289.79 126.06 76.69 

294.81 126.21 75.36 

302.25 126.31 74.29 

312.11 126.41 73.59 

326.87 126.4 73.71 

346.59 126.18 75.62 

366.45 125.89 78.18 

31\6.44 125.tl 78.89 

31\4.8 148.87 81.49 

365.74 148.45 85.2 

346.55 14S.05 M.72 

327.23 147.84 90.56 

312.71 147.91 90. 

303.05 148.08 811.49 

295.85 148.3 86.5 

291.11 1411. 55 84.31 

288.98 148.85 81.61 

291. 68 149.11 79.38 

296.52 149.25 78.1 

l 303.69 149.37 77.06 

313.19 149.44 76.39 

,j 327.41 149.43 76.5 

346.41 149.22 78.34 

I 

365.54 1411.94 80.81 

384.8 148.87 81. 49 

383.16 171. 92 84.1 

r 

.-- 364.82 171. 52 87.67 

346.36 171.13 91. 05 

327.78 170.93 92.82 

313.81 171. 92.28 

; 304.52 171.16 90.82 

j 297.59 171. 35 88.91 

I I 293.03 171.61 86.111 . ! 290.99 171.91 84.21 

293.58 172.15 82.06 

298.24 172.29 80.83 

305.13 172.4 79.113 

314.27 172.47 79.19 

327.95 1~;~.46 79 .29 

346.23 172.26 81. ill. ... 364.63 171.99 83.44 

383.16 171. 92 84.1 

381. 52 194.97 86.7 

363.91 194.59 90.13 

346.17 194.22 93.38 

3211. 32 194.03 95.011 

314.91 194.09 94.56 

305.911 194.24 93.16 

299.33 194.45 91. 33 

294.95 194.68 89.31 , 292.99 lSI4.96 86.S1 

295.48 195.19 84.75 

299.95 195.33 83.56 

306.57 195.44 82.6 

. j'. 315.35 115.51 81.98 

32!1.49 l'J5.49 82.09 

346.05 li5.3 83.79 

36:;.73 1~5.Dtl 86.07 

,I . , I 381.52 174.97 86.7 

! 379.88 2ill.03 89.3 

I 

I 

I 

, I : I ~ I ,., 

,'1 

:.\ , ' : 

I , / , 

t 

I~ !'I I , 

/ 123 t:- I .. ~ 
I 

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--

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I 

j 

I 

/ 

I / . 

,/ 

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i 

362.99 

345.99 

321L37 

316.01 

307.45 

301.07 

296.87 

294.99 

297.38 

301.67 

305.01 

316.43 

329.03 

345.87 

362.82 

379.88 

378.24 

3':'2.07 

3~ 5 .8 

3l9.42 

317.11 

308.92 

302.81 

298.79 

296.99 

299.28 

303.38 

309.45 

317.51 

329.57 

345.69 

361.91 

378.24 

376.6 

361.16 

345.61 

329.97 

3111. 21 

310.3S 

304.55 

300.71 

298.99 

301.17 

305.09 

310.9 

318.59 

330.11 

345.51 

361. 

376.6 

17.0 

391. 3601 

369.1799 

347.1399 

325.2500 

308.8701 

297.9199 

289.6699 

284.0901 

280.9800 

217.66 92.59 

217.3 95.71 

217.12 97.34 

217.18 96.34 

217.33 95.5 

217.53 93.74 

217.74 91.3 

213.02 89.41 

218.24 87.43 

218.37 86.3 

215.47 85.38 

218.54 84.78 

213.53 34.&8 

218.34 86.51 

218.10 88.7 

218.03 89.3 

241. 08 91. 91 

240.72 95.06 

240.39 98. 04 

240.21 99.6 

240.27 99.13 

240.41 97.84 

240.6 96.15 

240.81 94.3 

240.07 92.01 

241. 28 90.12 

241. 41 89.03 

241.5 88.15 

241. 57 87.58 

241. 56 37.63 

241.33 89.23 

241.15 91. 33 

241.03 91. 91 

264.13 94.51 

263.79 97.52 

263.47 100.37 

263.3 101.86 

263.35 101.41 

263.49 100.18 

263.63 98.57 

263.&5 96.8 

264.12 94.61 

2(,4.33 92.8 

264.44 91.76 

264.54 90.92 

264.6 90.38 

264.59 90.47 

264.4:: 91. 96 

264.2 -:3.96 

264.13 94.51 

10.0 -56.~500 71.0700 

-56.7400 70.2900 

-57.0600 67.4400 

-57.3000 65.3200 

-57.3200 65.2000 

-57.2300 65.9700 

-56.1000 67.1600 

-56.9300 68.6400 

-56.6400 71.2100 

124 
/ 

r 

1.'/ 

I' ./ I 

I 

I 

.I 

/ 

i .. ," "-

r--' " 

I 

I 

" 

,-t'. 

f'i 

, 

I .. , 

i' 

i 

I. 

/i 

I . I • ,1/ . " 

i 

/ i ~ ~! 

i J /~. 

283.4299 -56.2900 

288.8899 -56.0000 297.189~ -55.7400 

308.3101 -55.5500 

325.0400 -55.4700 

347.2900 -55.7100 

369.3999 -56.1700 

391.3601 -56.6500 

389.7200 -79.7100 

368.2700 -79.7900 

346.9600 -aO.1000 

325.7900 -se.3300 309.~500 -80.3500 

299.3601 -80.2600 

291.3799 -00.1300 

285.9900 -79.9700 

282.9800 -79.6900 

285.3501 -79.3500 

290.6299 -79.0800 

298.6499 -78.8300 

309.4099 -78.6400 

325.5901 -78.5700 

347.1101 -78.0000 

368.4800 -79.2400 

389.7200 -79.7100 

3S8.0aOl -102.7600 

367.3601 -102.8400 

346.7800 -103.1400 

326.3301 -103.3700 

311.0300 -103.3800 

300.8000 -103.3000 

293.0901 -103.1700 

287.8899 -103.0200 

284.9800 -102.7500 

287.27DO -102.4200 

292.3701 -107..1500 

300.1201 -101.9100 

310.5100 -101.7300 

326.1299 -101.6600 

346.9199 -101.8800 

367.5701 -102.3100 

388.0801 -102.7600 

386.4399 -125.el00 

366.4500 -125.8900 

346.5901 -126.1800 

326.8701 -126.4000 

312.1101 -126.4100 

302.2500 -126.3300 

294.8101 -126.210G 

289.7900 -126.0600 

286.9800 -125.8000 

289.1899 -125.4800 

294.1101 -125.2300 

301.5901 -124.9900 

311.6101 -124.8200 

326.6799 -124.7500 

346.7300 -124.9700 

366.6499 -125.3800 

386.4399 -125.~100 

384.8000 -148.8700 

i ..,...~.,.. ____ ._~ ... _ ....... _ '_~""'J. _--...• --.-:- :--..... ___ ~ ..... --~--.-..... ----_. 

74.320Q 

76.8400 

79.1300 

80.8800 

81.5200 

79.4000 

75.3500 

71. 0700 

73.6800 

72.9200 

70.1700 

6!1.1200 

67.9900 

65.7400 

69.900Cl 

71.3200 

73.3100 

76.11200 

79.2600 

81.4700 

83.1600 

83.7800 

81. 7300 

77 .3100 

73.6800 

76.211ilO 

75.5500 

72.8900 

70.9100 

70.7900 

71.5100 

72.6300 

74.0100 

76.4100 

79.3200 

81.6700 

83.8100 

85.4400 

116.0400 

84.0600 

aO.2800 

76.<:lSOO 

78.8900 

711. 1S00 

75.6200 

73.7100 

73.5'100 

74.2900 

75.3600 

76.6900 

79.0100 

111.8200 

1$4.0900 

86.1500 

87.7200 

SS.3ilOO 

86.3900 

112.7400 

78.8900 

81.4900 

- --.~--~ .. -....... _--.. ----_ .. -,' .. -

ORIGfN,~L PAnE'iS 

OF POOR QUALIT'l 

125 
"-"-, 

"-

.... -"-, 

365.5400 -1',8.9400 80.8100 

346.4099 -149.2200 78.3400 

327.4099 -149.4300 76.5000 

313.1899 -149.4400 76.3900 

303.6899 -149.3700 77.0600 

/ 296.5200 -149.2500 78.1000 

I , 291. 6799 -149.1100 79.3800 

288.9800 -148.1I500 81.6100 

291.1101 -14I1.:i500 84.3100 

295.8501 -148.3000 86.5000 

303.0500 -141300800 88.4900 

312.7100 -1(,7.9100 90.0000 

327.2300 -147.8400 90.5600 

346.5500 -148.0500 M.7200 

365.7400 -141304500 85.2000 

384.8000 -148.8700 81.4900 

383.1599 -171.9200 84.1000 

364.6299 -171.9900 83.4400 

346.2300 -172.2600 81. 0600 

327.9500 -172.4600 79.2900 

314.2700 -172.4700 79.1900 

305.1299 -172.4000 79.8300 

298.2400 -172.2900 80.8300 

293.5801 -172.1500 82.06110 

290.9900 -171.9100 &4.2100 

293.0300 -171. 6100 86 .ln~O 

297.5901 -171.3800 8lL 9100 

304.5200 -171.1600 90.8200 

313.8101 -171.0000 92.2800 

( 327.7800 -170.9300 92.8200 

346.3601 -171.1300 91. 0500 

364.8201 -171.5200 87.6700 

383.1599 -171.9200 84.1000 

3S1. 5200 -194.9700 86.7000 

363.7300 -195.0400 86.0700 

346.0500 -195.3000 83.7900 

328.4900 -195.4900 82.0900 , 315.3501 -195.5100 81.9800 I 306.5701 -195.4400 82.6000 

299.9500 -}<"').3300 33.5600 

295.4800 -B5.1900 84.7500 

292.9900 -194.9600 36.8100 

294.9500 -194.6800 89.3100 

299.3301 -194.4500 91. 3300 

305.980(1 -194.2400 93.1600 

314.9099 -194.0900 94.5600 

328.3201 -194.0300 95.0800 

346.1699 -194.2200 93.3300 

363.9099 -194.5900 90.1300 

381.5200 -194.9700 86.7000 

379.8799 -2UI. 0300 39.3000 

362.8201 -211L :'(100 llll.7000 

345.8701 -218.34IJO 86.5100 

329.0300 -213.5300 84.8800 

316.4299 -211L 5400 84.7800 

308.0100 -2111. 470il 85.3800 

301.6699 -218.3700 86.3000 

297.3799 -21~.2400 87.4300 

294.9900 -213.0200 89.4100 

296.8701 -217.7400 91.11000 

126 

! 
.-

. .c .. :--" '~."'" ",. w ..... .-_ .~.--. '"':::'::..::: .• :l: .. : .. : .. ~~-::: ---;: --.. -'"""" ,.-.<-:-:-:-:: ... ;:;:::;::=:::;:::.:....:-...=:.:z..-:::-:::-::' 

'.~.~ 

~ 

ORf0.~?·!:'\L r-::~.r:::··l5" 

OF f';;~'<{ Q'_i}:,~:TY 

301. U101 -217.5300 93.7400 

\ 307.4500 -217.3300 95.5000 

316.0100 -217.18nO 96.8400 

\ 328.8701 -217.1200 97.3400 , 345.9900 -217.3000 95.7100 

362.9900 -217 .6600 92.5900 

379.8799 -218.0300 '9.3000 

,)78.2'100 -241.0800 91.9100 

361. 9099 -241.1S00 91. 3300 

345.6899 -241. 3800 89.2300 

329.5701 -241.5(1)') 87.6800 

317.5100 -241. 5700 87.S800 

309.4S00 -241.S000 88.1S00 

31..L3799 -241.410" 89.0300 299.~800 -241.2800 90.1200 

296.9900 -240.0700 92.0100 

,n.7900 -240.8100 94.3000 

302.8101 -240.6000 96.1500 

308.9199 -240.4100 97.8400 

317.1101 -240.2700 99.1300 

329.4199 -240.2101) 99.6000 

345.8000 -240.::;900 98.0400 

362.0701 -240.7200 ~S.0600 

37lS,2400 -241. 0800 91.9100 

376.6001 -264.1299 94.5100 

361.0000 -264.2000 93.9600 

345.510C -26".4199 91. 9600 

330.1101 -264.5901 90.4700 

318.5901 -264.6001 90.3800 

~'. .\ .. 310.8999 -264.5:'OU 90.9200 

; 305.0901 -264.4399 91.7600 

301.1699 -264.3301 92.80:10 

298.9900 -26'.1201 94.6100 

300.7100 -263.8799 96.8000 

304.5S00 -263.6799 98.5700 

310.379:) -263.4900 100.1800 

318.2100 -263.3501 101.4100 

329.9700 -263.30n.0 101.8600 

345.6101 -263.4700 100.3700 

361.1599 -263.7900 97.5200 

376.6001 -264.1299 94.5100 

8. 2. 

271- O. 72.8 

2&4.09 O. 68.64 

289.67 O. 67.16 

297.92 O. 65.97 

308.87 O. 65.2 

325.25 O. 65.32 

347.14 O. 67.44 

391.7 O. 74.4 

271. 29.2 72.8 

284.09 29.2 68.64 

289.67 29.2 67.16 

297.92 29.2 6S.97 

308.87 29.2 65.2 32~.25 29.2 65.32 

347.14 29.2 67.44 

391. 7 28. 74.4 

8.0 '1 0 

391. 7 -0.0000 74.4 

/ 

/ 

/ / 

,----' 

~ 127 

.. 
-;'( . 

"., :.. .: 

, ....:---.\ , 'of 

" ... ' 

~ '. .' 

" i 

I 

I 

i 

I 

I 

I 

I 

/ 

! "j 

I' 

I ", 

.' 

'" 

. : ........... : 

'. 

. ~ .. --' .--' 

'/ 

.I 

I, 

\ ~ .. --

347.1j99 -0.0000 

325.2500 -0.0000 

308.8101 -0.0000 

297.9199 -0.0000 

289.6699 -O.OO~O 

~84.0901 -0.0000 

271.0000 -0.0000 

391.7 -28. 

347.1399 -29.2000 

325.2500 -29.2000 

301l.8701 -29.2000 

297.9199 -29.2000 

289.6699 -29.2000 

284.0901 -29.2000 

271.0000 -29.2000 

17. 2. 

391.7 28. 

376.6 38.9 

347.29 38.' 

325.04 38.9 

301l.31 !8.9 3~0. 3S.9 

289. 35.22069 

282. 32.87931 

271. 2\'.2 

284.09 :>9.2 

289.67 2'1.2 

297.92 29.2 

308.87 29.2 

325.25 ~9.2 

347.14 29.2 

369.18 28.60646 

391.7 28. 

391.36 56.65 

369.4 56.17 

347.29 55.71 

325.04 55.47 

303.31 55.~:; 

297.19 55.74 

288.89 56. 

2113.43 5~.29 

280.98 56.64 

284.09 56.93 

289.67 56.1 

297.92 57.23 

308.87 57.3~ 

325.25 57.3 

347.14 57.06 

369.18 56.7(t 

391.36 56.65 

17.0 

391.7000 

369.1799 

347.1399 

~25.25DD 

:lOt1.8701 

297.9199 

289.6699 

284.0901 

271. 0000 

2.0 

-<:8.0000 

-28.11065 

-29.2000 

-,'1.2000 

-::~.2000 

-~9.2000 

-;:9.2000 

-?9.2000 

-29.2000 

67.4400 

65.3200 

65.2000 

65.9700 

67.1600 

68.6400 

7Z.8000 

74.4 

67.4400 

65.3200 

65.2000 

(,5.9700 

67.1600 

61LfftOO 

72.8000 

74.~ 

85. 

85. 

8S. 

85. 

85. 

80.37241 

77.42759 

12.4 

68.64 

67.16 

65.97 

65.2 

65.32 

67.44 

70.1111251 

74.4 

71. 07 

75.35 

79.4 

1I1.52 

1I0.S8 

79.13 

76.84 

74.32 

71.21 

68.64 

67.16 

65.'1' 

65.2 

65.32 

67.44 

70.29 

71.07 

74.4000 

70.8825 

67.4400 

65.320D 

65.2000 

65.9700 

67.1600 

68.6400 

72.8000 

128 
282.0~00 -32.8793 77 • ~276 

2ln.0000 -35.2207 80.3i~4 

300.0000 -31L 9000 85.0000 

308.3101 -38.9000 B5.o000 

325.0400 -3a.90CO 85.0000 

347.2S00 -38.9000 d5.000o 

376.6001 -38.9000 as. DODD 

391.7000 -21S.0000 74.4000 

39L3601 -56.6500 71.0700 

369.1799 -56.7400 70.2900 

347.1399 -57.0600 67.4400 

325.2500 -57.3000 65.3200 

305.8701 -5~' .3200 65.2000 

297.919'11 -57.2300 65.9700 

2:;9.6699 -56.1000 67.1600 

284.0901 -S6.9300 61L 6400 

2t1o. noo -56.6400 71.2100 

283.4299 -56.2900 74.3200 

288.8899 -56.0000 76.8400 

297.1899 -55.7400 79.1300 

3015.3101 -55.5500 80.sao:! 

325.0400 ~SS.4700 81. 5200 

347.2900 -55.7100 79.4000 

369.3999 -56.1700 75.3500 

391.3601 -56.6500 71. 0700 ,'- 9. 3. I 175.6 79.9 120.3 

175.6 79.9 120.3 

175.6 79.9 120.3 1~S.6 79.9 120.3 

175.6 79.9 120.3 

115.6 79.9 120.3 

175.6 79.9 120.3 

175.f. 79.9 120.3 

175.6 79.9 120.3 

211. 9 79.9 101.5 

211. 5 64.a 107.7 

210.4 58.6 122.a 

209.3 64.a 137.8 

208.9 79.9 144.0 

209.3 95.0 137.S 

210.ft 101.2 122.8 

211.5 95.0 107.7 

211. 9 79.9 101.5 

225.9 79.9 98.3 

225.3 61.9 105.7 

224.0 54.4 123.7 

222.8 61.9 141. 7 

222.2 79.9 14'),2 

222.8 97.9 141. 7 

224.Q 105.4 123.7 

225.3 97.9 10S.7 

225.9 79.9 98.3 

248.4 79.9 99.4 

247.9 61.5 107.0 

246.6 53.9 125.3 

245.3 61.5 143.7 , 244.7 79.9 151. 3 , 245.3 98.1 143.7 

246.6 105.9 125.3 

-,' 

----:. , 

" 

129 
/ 

I 

247.9 98.3 107.0 

248.4 79.9 99.4 

267.1 79.9 102.4 

266.6 62.6 109.5 

265.3 55.5 126.7 

264.1 62.6 143.9 

263.6 79.9 151. 0 

264.1 97.2 143.9 

265.3 104.3 126.7 

266.6 97.2 109.5 

267.1 79.9 10Z.4 

299.3 79.9 104.7 

298.8 62.6 111.8 

297.6 55.5 lZ9.0 

:!96.3 62.6 146.2 

295.8 79.9 153.3 

296.3 97.2 146.2 

297.6 104.3 129.0 

298.8 97.Z Ill.! 

299.3 79.9 104.7 

700.7 79.9 133.4 

700.2 62.6 140.6 

699.0 55.S 157.! 

697.7 62.6 175.0 

697.2 79.9 182.1 

697.7 97.2 175.0 

~, 699.0 104.3 157.8 

700.2 97.2 140.6 

700.7 79.9 133.4 

1000. 79.9 133.4 

1000. 6Z.6 140.6 

1000. 55.5 lS7.! 

11100. 6Z.6 175.0 

1000. 79.9 182.1 

~I 1000. 97.2 175.0 

1000. 104.3 157.8 

1000. 97.Z 140.6 

1000. 79.9 133.4 

9. 8. 

175.60 -79.90 lZ0.30 

175.60 -79.90 1Z0.30 

175.60 -79.90 1Z0.30 

175.60 -79.CiO lZ0.30 

175.60 -79.90 120.30 I 

~ 175.60 -79.90 lZ0.30 

175.60 -79.90 120.30 175.~0 -79.90 120.30 

175.60 -79.90 120.30 

211.90 -79.90 101. 50 

211.50 -95.00 107.70 

Z10.40 -101. 20 122.80 

209.30 -95.00 137.80 

208.90 -79.90 144.00 

209.30 -64.80 137.80 

210.40 -58.60 122.80 

211.50 -64.80 107.70 

211. 90 -79.90 101.50 

225.90 -79.90 98.30 

225.30 -97.90 105.70 

224.00 -105.40 lZ3.70 

130 
/ -', -, 

I' 

!' 

;r-·-----· ---.---.- _.' 

-- -- ~-." 

--_ .. ,._--... .•. --.,., 

!--..cl 

.; 

/ OmG\\;~L r :.{1:.: :;::1 / OF. r-OOH Q\;;:'~i..n y / 

I 

/ 

.' 

1- 222.80 -97.90 141.70 

222.20 -79.90 149.20 i 222.80 -61.90 141.70 I 224.00 -54.40 123.70 

225.30 -61.90 105.70 

225.90 -79.90 98.30 

248.40 -79.90 99.40 

247.90 -91L 30 107.00 

246.60 -105.90 125.30 

245.30 -98.30 143.70 

244.70 -79.90 151.30 

245.30 -61.50 143.70 

246.60 -53.90 125.30 

247.90 -61.50 107.00 

248.40 -79.90 99.40 

267.10 -79.90 102.40 

266.60 -97.20 109.50 

265.30 -104.30 126.70 

264.10 -97.20 143.90 

263.60 -79.90 151.00 

264.10 -62.60 143.90 

265.3(1 -55.50 126.70 

266.60 -62.60 109.50 .,- 267.10 -79.90 102.40 ..-- 299.30 -79.90 104.70 -- ,,- 29a.80 -97.20 l11.aO 

297.60 -104.30 129.00 

296.30 -97.20 146.20 

295.80 -79.90 153.30 

296.30 -62.60 146.20 

297.60 -55.50 129.00 

291L80 -62.60 111.80 .... 299.30 -79.90 104.70 

700.70 -79.90 133.40 

700.20 -97.20 140.60 

i 699.00 -104.30 157.eo 

697.70 -97.20 175.00 

I 697.2C -79.90 182.1U 

697.70 -62.60 175.00 

I. 699.00 -55.50 157.80 

700.20 -62.60 140.60 

700.70 -79.90 133.'.0 

1 .. ''"': "" 1000,00 -79.90 133.e.O 

; \; I· 1000.00 -97.21) 140.60 

1000.00 -1')'.3G \57.bO 100~. ju -97.20 175.00 

lOOr.. ~" -]'i.90 :52.10 

1000.CO -62.60 175.00 

1000.00 -55.50 1~7.S0 

.-,- 1000.00 -62.60 140.60 

! 1000.00 -77.90 133.40 

MULT 

2. 

II. 9. 7. 1. 10. O. 

2115.35 79.63 74. 3ft 

290.63 79.59 74.68 

298.65 79.54 75.16 

309.41 79.49 75.6 

325.59 79.45 75.95 

347.11 79.45 75.96 

, 

-J. 

i 

I / I 

I I 

/ 131 

~ / 

/ 

/ ~ 
/ 

-- _ . .:.._-. 

~ 

~ 

~-

., . .' 

:' .' . 

'-, .'->.- .,.. .. - " 

,.-

~ 

- /'.' 

.,~'" ~ -

/ 

/ 

/ 

..... ...;;.... '. 

,: / / , .( .. 

368.48 79.52 

389.72 79.71 

411.29 79.71 

454.51 79.71 

90JO. 79.71 

287.27 102.69 

292.37 102.65 

300.12 102.6 

310.51 102.55 

326.13 102.51 

346.92 102.51 

367.:'7 102.58 

388.08 102.76 

408.92 102.76 

450.66 102.76 

9000. 102.76 

289.19 125.74 

294.11 125.71 

301. 59 125.60 

311.61 125.61 

326.6S 125.57 

346.73 125.57 

366.65 125.64 

386.44 12~.:n 

406.54 125.81 

446.lU 125.lIl 

9000. 125.81 

291.11 148.8 

295.85 14&.77 

303.05 148.72 

312.71 148.67 

327.23 143.6ft 346.55 148.64 

365.74 148.7 

384.8 148.87 

404.17 148.87 

4l12.96 148.87 

9000. 14&.87 

293.03 171.86 

297.59 171.82 

304.52 171.78 

313.81 171.73 

327.73 171. 7 

346.36 171. 7 

'364.82 171.76 

383.16 171.92 

401.79 171. 92 

439.11 171.92 

9000. 171.«;2 

294.95 194.91 

299.33 19ft.88 305.98 194.84 

314.91 194.79 

328.32 194.76 

346.17 194.76 

363.91 194.&2 

3tH. 52 194.97 

399.41 19(1.97 

435.26 194.97 

9000. 194.97 

74.37 

73.6a 

71. 98 

69.72 

-165.62 

76.92 

77 .25 

77.71 

78.13 

78.48 

78.49 

77 .92 

76.28 

74.64 

72.46 

-162.88 

79.5 

79.82 

80.26 

80.67 

81. 

81. 01 

80.46 

78.89 

77.31 

75.2 

-160.15 

82.08 

a2.39 

82.112 

8J.21 

83.53 

83.54 

8l.01 

81.49 

79.97 

77.94 

-157.ftl 

M.67 

a4.96 

85.37 

85.75 

86.06 

86.07 

85.56 

84.1 

1:2.63 

&0.68 

-154.67 

87.25 

87.53 

87.93 

&8.29 

88.58 

&8.59 

88.1 

86.7 

85.29 

83. 41 

-l51. 93 

132 

i 

i· 

.' 
---

/' 

•• A, 

( 

- j ,r--- ! 

I 

, 

,r--" l 

I I 

i 

I 

, 

I 

I 

I 

, 

l 

I 

I 

'--' I . I 

j. 

~/ 

/ 

.' 

,,'/ ,/ 

.' 

I .. ;'. 

. ~ .. 

.. ,.0

' 

""<:: 

\ 

) _ ..... 

/. ./,-::.,,.... 

~-- ,.--..... 

. Y 

296.37 217.97 

301.07 217.94 

307.45 217.89 

316.01 217.85 

.321S.IH 217.82 

345.99 217.1>2 

362.99 217.87 

379.88 218.03 

397.04 2 ilL 03 

431.41 218.03 

9000. 218.03 

298.79 241.02 

302.nl 240.99 

308.92 240.95 

317.11 240.92 

329.42 240.89 

345.8 240.88 

362.07 240.93 

378.24 241.08 

394.66 241. 03 

427.56 241. 08 

9000. 241. 08 

300.51 261. 77 

304.37 261. 75 

310.24 261.71 

llS.1 261. 67 

329.91 261. 64 

345.63 261.64 

361.25 261.69 

376.76 261.83 

392.52 261.IU 

424.1 261.83 

9000. 261.83 

.050192 .085453 

.10887 

388.93 91.17 

387.29 114.22 

385.64 137.27 

384. 160.32 

382.36 183.37 

380.72 206.42 

379.0S 229.47 

377 .44 252.52 

11. 9. 

285.35 -79.63 

290.63 -79.59 

298.65 -79.54 

309.41 -79.49 

325.59 -79.45 

347.11 -79.45 

366.48 -79.52 

389.72 -79.71 

411.29 -79.71 

454.51 -79.71 

9000. -79.71 

287.27 -102.69 

292.37 -102.65 

300.12 -102.6 

310.51 -102.55 

326.13 -102.51 

89.83 

90.1 

90.48 

90.153 

91.11 

91.12 

90.65 

89.3 

87.95 

86.15 

-149.19 

92.41 

92.67 

93.03 

93.37 

93.64 

93.64 

H.2 

91. 91 

90.62 

88.89 

-146.45 

94.73 

94.98 

95.33 

95.65 

95.91 

95.92 

95.49 

94.25 

93.01 

91. 36 

-143.98 

.120618 

74.97 

77 .58 

80.18 

82.78 

85.39 

87.99 

90.59 

93.2 

7. 

74.34 

74.68 

75.16 

75.6 

75.95 

75.96 

74.37 

73.68 

71. 98 

69.72 

-165.62 

76.92 

77 .25 

77.71 

78.13 

78.43 

/ 

;" 

I / 

ORlC';N ~.,- i"'." I::. ,:.~ 

Or- F~I~;'; (; " " " 

.172921 .242018 

.on89 -.10636 

.07689 -.10636 

.07889 -.10636 

.078159 -.10636 

.07889 -.10636 

.07889 -.10636 

.07ES9 -.10636 

.07889 -.10636 

1. 10. 

133 

.219928 

.99119 

.99119 

.99119 

.99119 

.99119 

.99119 

.99119 

.99119 

O. 
/ 

I 

i 

I 

,/ 

/ / i' ~ ,/ "0 

/ - I 

'I J 

,~ .-

.-~-- .~ 

,\ .' 

-

-

.,....:-

( ,.../' '/ 

/ 

, ~, 

,- /' 

" ,,I ! -i 

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, ~ r. " ,," 

Ii" 

: ! J.", 

, 

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/ 

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I i . ! 

! 

" I 

/ 

I 

/ 

-j 

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i, ' , , 'r' ',' ! 

,. ,,' 

~. 

Q , 

i 

346.92 -102.51 

367.57 -102.53 

383.03 -102.76 

40lL 92 -102.76 

450.66 -102.76 

9000. -102.76 

239.19 -125.74 

294.11 -125.71 

301.59 -125.66 

311. 61 -125.61 

326.611 -125.57 

346.73 -125.57 

366.65 -125.64 

386.4" -125.81 

406.54 -125.81 

446.81 -125.31 

9000. -125.31 

291.11 -148.8 

295.85 -148.77 

303.05 -148.72 

312.71 -148.67 

327.23 -148.64 

346.55 -143.64 

365.74 -148.7 

384.1! -148.87 

404.17 -148.87 

442.96 -143.37 

9000. -148.87 

293.03 -171.136 

297.59 -171.82 

304.52 -171. 78 

313.lU -171.73 

327.73 -171.7 

346.36 -171.7 

364.82 -171.76 

383.16 -171.92 

401.79 -171.92 

439.11 -171.92 

9000. -111.92 

294.95 -I'J •• 91 

299.33 -194.83 

305.98 -194.84 

314.91 -194.79 

328.32 -194.76 

346.17 -194.76 

363.91 -194.82 

381.52 -194.97 

399.41 -194.97 

435.26 -194.97 

9000. -194.97 

296.87 -217.97 

301. 07 -217.94 

307.45 -217.89 

316.01 -217.85 

328.&7 -217.82 

345.99 -217.112 

362.99 -ZIT.87 

37?.!IL' -21~1. 03 

397.04 -21.'1.03 

431.41 -21~.03 

78.49 

77.92 

76.28 

74.64 

72.46 

./ 

/' 

-162.33 

79.5 

79.82 

30.26 

80.67 

81. 

IH.01 

30.46 

78.U 

77.11 

7S.2 

-160.15 

82.03 

82.39 

82.32 

83.21 

83.53 

83.54 

83.01 

81. 49 

79.97 

77.94 

-157.41 

84.67 

lI4 • 96 

85.37 

85.75 

86. 06 

86.07 

85.56 

84.1 

82.63 

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87.25 

87.53 

137.93 

88.29 

88.SIS 

88.59 

88.1 

86.7 

85.29 

83.41 

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89.83 

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304.37 -261.75 94.93 ., 310.24 -261.71 95.33 I 

318.1 -261. 67 95.65 

329.91 -261.64 95.91 .. -;' 345.63 -261.64 95.92 

361. 25 -261.69 95.49 

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424.1 -261.83 91. 36 

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CASE 

RSRA FUSELAGE AND WINGS. WING INCIDENCE 5.52 DEGREES 

J D COWAH AERO RESEARCH ORGH 7440 EXT 7834 

GEOM 

3. 634. 1- -1, 

SOUR 

16 • 7. 4. 

36. O. 95.9 

36. O. 95.9 

36. 0.0 95.9 

36. 0.0 95.9 

36. 0.0 95.9 

36. 0.0 95.9 

36. 0.0 95.9 

58.8 0.0 110.2 

511.11 16.9 108.1 

SIl.1! 22.5 106. 

511.11 22.5 96.2 

58.S 22.5 116.4 

58.11 16.9 S2.3 

SS.II 0.0 112.3 

81.5 0.0 119.9 

81.5 22.1 116.4 

81.5 29.5 113. 

81.5 29.5 99 . 81.5 29.5 85. 

81.5 22.1 73.1 

81.5 0.0 7S.1 

120.9 O. 147.6 

120.9 28.4 136, 7 

120.9 37.11 125.9 

120.9 37.8 108. 

120.9 37.S 90.7 

120.9 2S.(" 74.8 

120.9 O • 14.8 

7. 6. 

120.9 O. 147.6 

120.9 28.4 136.7 

120.9 37.8 125.9 

120.9 37.11 lOS. 

120.9 37.8 90.7 

120.9 28.4 74.11 

120.9 O. 74.11 

lll. O. 14S.9 

133. 29.2 141L 9 

133. 38.9 129.9 

133. 31L9 110.8 

lll. 38.9 91.S 

133. 29,2 72.1! 

133. O. 72.S 

175.3 12.1 148.9 

175.3 29.2 148.9 

175.3 311.9 129.9 

175.3 38.9 110.8 

175.3 31L9 91.8 

137 
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175.3 29.2 72.8 

175.3 o. 72.8 

209.3 21. 9 148.9 

209.3 29.2 148.9 

209.3 38.9 129.9 

209.3 38.9 110.8 

209.3 38.9 91.8 

209.3 29.2 12.8 

209.3 o. 72.S 

222.3 22.7 148.9 

222.3 29.2 14!L 9 

222.3 38.9 129.9 

222.3 38.9 110.G 

222.3 38.9 91.8 

222.3 29.2 72.8 

222.3 o. 72.8 

271. 22.7 148.9 

271. 29.2 14G.9 

271. 38.9 129.9 

271. 38.9 110.8 

271. 38.9 91.8 

271. 29.2 72.8 

271. o. 72.8 

6. 4. 

271. 22.7 148.9 

271. 29.2 148.9 

271. 38.9 129.9 

271. 38.9 110.8 

271. 38.9 91.8 

271. 29.2 12.8 

300. 22.7 141L 9 

300. 29.2 148.9 

300. 3S.9 129.9 

300. 3/l.9 110.8 

300. 3S.9 91.8 

300. 38.9 85. 

376.6 17.11 148.9 

376.6 29.2 148.9 

376.6 38.9 129.9 

376.6 38.9 110.8 

376.6 38.9 91.8 

376.6 38.9 85. 

391. 7 15.7 147.3 

391. 7 28. 141.3 

391. 7 37.3 129. 

391. 7 37.3 110.8 

391. 7 37.3 92.6 

Hl.7 28. 74.4 

7. S. 

391. 7 15.7 147.3 

391.7 28. 147.3 

391.7 37.3 129. 

391. 7 37.3 110.8 

391. 7 37.3 92.6 

391.7 28 • 74.4 

391. 7 O. 74.4 

445.7 7.871145 143.46 

445.7 24.5 143.46 

445.7 32.7 127.2 

445.7 32.7 110.8 

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600. 

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600. 

600. 

600. 

1000. 

1000. 

1000. 

1000. 

1000. 

1000. 

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7. 

133. 

133. 

133. 

133. 

133. 

133. 

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175.3 

175.3 

175.3 

175.3 

175.3 

175.3 

175.3 

209.3 

209.3 

209.3 

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209.3 

209.3 

209.3 

222.3 

222.3 

222.3 

222.3 

222.3 

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271. 

271. 

271. 

271. 

271. 

271. 

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12.1 

12.1 

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21.1 

22. 

22. 

20.2 

21. 9 

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19.6 

22.7 

22.7 

22.7 

22.7 

22.7 

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22.7 

22.7 

22.7 

22.7 

22.7 

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77 .,. 

77 .3 

139.6 

139.6 

125.4 

110.8 

96.2 

81.3 

81.3 

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131. 

120.9 

110.8 

100.4 

89.9 

89.9 

131. 

131. 

120.9 

110.8 

100.4 

89.9 

89.9 

141S,9 

148.9 

148.9 

14El.9 

148.9 

148.9 

148.9 

165.9 

165.9 

163.6 

161.4 

157.4 

153.8 

148.9 

179.7 

179.7 

175.5 

171.6 

164.3 

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148.9 

181. 3 

181. 3 

181.3 

174.8 

166.4 

158.9 

148.9 

189.2 

189.2 

189.2 

181.1 

170.7 

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148.9 

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139 
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300. O. 

300. 

300. 

300. 

300. 

300. 

300. 

348.6 

348.6 

341S.6 

348.6 

348.6 

348.6 

348.6 

376.6 

376.6 

376.6 

376.6 

376.6 

376.6 

376.6 

391.7 

391. 7 

391. 7 

391. 7 

391. 7 

391. 7 

391. 7 SO~. 

500. 

500. 

500. 

500. 

500. 

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22.7 

22.7 

22.7 

22.7 

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36. 

36. 

36.0000 

36.0000 

36.0ooQ 

36.0000 

36.0000 

51S.aOtO 

58.8 

58.8000 

58.8000 

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58.8000 

81. 5000 

81.5 

81.5000 

a1.5000 

81.5000 

81.5 

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120.900) 

120.9 

120.9000 

O. 

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19.5911 

19.5911 

19.5911 

19.59'.1 

19.5911 

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15.3 

17.1S 

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17 .8 

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15.7 

15.7 

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193.8 

193.8 

193.8 

184.8 

173.3 

16!. 

148.9 

196.4 

196.4 

196.4 

186.9 

174.6 

163.6 

148.9 

188.1 

188.1 

188.1 

180.3 

170.1 

161. 0 

148.9 

182.9 

182.9 

1&2.9 

175.8 

166.5 

158.3 

147. 3 

139.6 

139.6 

139.6 

139.6 

139.6 

139.6 

139.6 

95.9 

95.9 

95.9000 

95.9000 

95.9000 

95.9000 

95.9000 

82.3000 

82.3 

86.4000 

96.2000 

106.0000 

1oa.1 

110.2000 

71L 1000 

78.1 

85.0000 

99.0000 

113.0000 

116.4 

119.9000 

74.8000 

74.8 

90.7000 

.'\ / 

140 
\ . 120.9000 -37.dUOO 108. 

120.9000 -37.1'.000 125.9000 

120.9 -2a.1f 136.7 

120.9000 -O.O(:JO lft7.6000 

7.0 6. 

lZO.9000 -0.0000 74.8000 

120.9000 -28. ::000 74.11000 

120.9000 -37.8000 90.7!!00 

120.9000 -37.8000 108. 

120.9000 -37.8000 125.9000 

120.9000 -23.4000 136.7000 

120.9000 -0.0000 147.6000 

133.0000 -0.000:1 72.800(1 

133.0000 -29.2000 72.8000 

133.0000 -38.9000 91.S000 

133.0000 -33.C;000 110.8000 

133.0000 -38.9~00 129.9000 

133. 0000 -29.2000 14&.9000 

133.0000 -0.0000 148.9000 175.~000 -0.0000 72.&000 

175.5000 -29.2000 72.8000 

175.3000 -38.9000 91.8000 

175.3000 -38.9000 110 .8000 

175.3000 -38.9000 129.9000 

175.3000 -29.2000 148.9000 

175.3000 -12.1000 148.9000 

209.3000 -0.0000 72.8000 ~ .. 

I 209.3000 -29.2000 72.8000 

209.3000 -3S.900U 91. 80tlO 

209.3000 -38.9000 110.8000 

209.3000 -38.9000 129.900J 

209.3000 -29.2000 148.9000 

209.3000 -21. 9000 148.9000 

222.3000 -0.0000 72 .SOOO 

222.3000 -29.2000 72.8000 

222.3000 -38.'>'000 91.8000 

222.3000 -38.9000 110.8000 

222.3000 -;8."000 129.9000 

222.3000 -29.2000 14&.9000 

222.3000 -22.7000 148.9000 

271. 0000 -0.0000 72.8000 

271. 0000 -29.2000 72.8000 

271. 0000 -:;a.9000 91.8000 

271. 0000 -38.9000 1l~.8000 

271.0000 -3!L 9000 12Q.900o 

271. 0000 -29.2000 148.9000 

271. -22.7 148.9000 

6. 4. 

271.0000 -29.2000 72.8 

271.0000 -38.9000 91.& 

271. 0000 -38.9000 110.8000 

271. 0000 -38.9000 129.9000 

271. 0000 -29.2000 148.9000 

271. 0000 -22.7000 148.9000 

300. -38.9 85. 

300. -38.9 91.3 

300. -38.9 110.3 

300. -38.9 129.9 

300. -29.2 148.9 

300. -22.7 148.9 

141 
.. ~. 

' .. to" 

376.6 -38.9 85. 

376.6 -38.9 91.8 

376.6 -38.9 110.8 , ' 

376.6 -38.9 129.9 .' ~ 376.6 -2?2 148.9 

376.6 -17.8 148.9 ~91. 7 -~IJ. 74.4 

391. 7 -37.3 92.6 

391. 7 -37.3 110.8 

391. 7 -37.3 129. '-- 391. 7 -211. 147.3 

391. 7 -15.7 147.3 

7. 5. 

... - .... 391.7000 -0.0000 74.4000 ", 391. 7:100 -28.0000 74.4000 - >:-- 391.7000 -37.3000 92.&000 

391.7000 -37.3000 110.1\000 

391.7000 -37.3000 129.0000 

391. 7000 -28.0000 147.3000 

391. 7000 -15.7003 147.3000 

445.7000 -0.0000 77 .8000 

445.7000 -24.5000 77 .8000 

445.7000 -32.7000 94.4000 ~~:-.-'- 445.7000 -32.7000 1H.8000 

445.7000 -32.7000 127.2000 

445.7000 -24.5000 143.4600 

445.7000-7.871745 143.4&00 

500.0000 -(!.Oooo 81.3000 

500.0000 -?1. 0000 81.3000 

'. 500.0000 -21L 0000 '/6.2000 

'c 500.0000 -28.0000 110.8000 

SOO.OOOO -28.0000 125.4000 

500.0000 -21.0000 139.6000 

500.0000 -0.0000 139.6000 '" - 600.000" -0.0000 89.9000 .. 600.0000 -13.5000 89.9000 

600.0000 -1&.0000 100.4000 

600.0000 -IS. 0000 110.8000 

" 

600.0000 -18.0000 120.9000 

:'},»" .. ... .... 600.0000 -13.5000 131.0000 !. 600.0000 -0.0000 131. 0000 >',> " 1000.0000 -0.0000 89.9000 " .. ,'~ -i. 1000.0000 -13.5000 89.9000 

1000.0000 -18.0000 100.4000 

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", .. , 1000.0000 -18.0000 120.9000 

1000.0000 -13.5000 131. 0000 

1000.0000 -0.0001! 131.0000 

7.0 10.0 

133.0000 -0.0000 148.9000 

133.0000 ;-0.0000 148.9000 

'~J 133.0000 -0.0000 14!1. 9000 

133.00ol0 -0.0000 148.9000 " 

• 133.0000 -0.001)0 1411.90('0 -~. 133.0000 -0.0000 148.9000 .--.~- ; , 133.0000 -0.0000 148.9000 " 

17S.30na -12.1000 1411. 9000 00' 175.3000 -12.1000 153.8000 

175.3000 "12.1000 157.4000 

175.3000 -12.1000 161.4000 

-. ~ _.~ _,&4 _ 142 
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175.3000 

175.3000 

209.3000 

209.30~0 

209.3000 

209.3000 

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209.3000 

209.3000 

222.3000 

222.3000 

222.3000 

222.3000 

222.300~ 

222.3000 

222.3000 

271.000~ 

271.0000 

271.0000 

271.0000 

271.0000 

271. GIlOO 

271.0000 

300.000C 

300.0000 

300.0000 

300.0009 

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HIS. 6001 >', 34lL 6001 

348.6001 

348.6001 

348.6001 

348.6001 

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376.6001 

376.6001 

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376.6001 

376.6001 

376.6001 

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391. 7000 

391.7000 

391.7000 

391. 7000 

391.7000 

391.7000 

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-22.7000 

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-16.9000 

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10. 

163.6000 

165.9000 

165.9000 

148.9000 

157.8000 

164.3000 

171.6000 

175.5000 

179.7000 

179.7000 

14ll. 9000 

158.9000 

166.4000 

174.8000 

!31.3000 

11ll.3000 

11n.3000 

148.9000 

161. .. 000 

170.7000 

lIU.1000 

189.2000 

189.2000 

189.2000 

148.9000 

163.0000 

173.3000 

134.8000 

193.8000 

193.3000 

193.8000 

148.9000 

163.6000 

174.6000 

186.9000 

196.4000 

196.4000 

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J48.1178a 55.67416 79.74264 

326.172011 55.19565 83.97866 

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324.81283 51.01911 67.113657 

346.80632 57.017<:5 61.85307 

369.01630 56.93522 611.57924 

391.17400 57.0n647 67.24026 

389.54160 80.12214 70.00121 

368.80521) 79.42183 76.14757 

347.90560 11L 15641 82.09122 

326.6836lv 78.29368 &6.18752 

310.52507 7&.18892 IH.11492 

299.65298 78.26270 86.46179 

291.44849 18.424117 85.02619 

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361L 11473 79.97587 71.29602 

389.54160 80.12214 70.00121 

381.90921 103.15781 72.76215 

367.8nOl7 102.48715 78.698118 

347.69332 101.83861) 84.43980 

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'" 311.58777 101.29053 89.29215 .~<'- 301.08651 lO1.36179 1)8.66130 

293.16185 101.51843 87.27467 

2"'7.85631 101.72189 115.42042 2a~.30330 102.03010 82.74512 

287.962QO 102.33165 1)0.07563 

293.01107 102.54278 73.2:l669 

300.57546 102.75166 76.35757 

310.68265 102.9"325 74.66149 

325.92561 103.09489 73.31912 

346.46829 103.09315 73.33454 "- 367.21316 103.01653 74.01280 .' '\, 387.90921 103.15781 72.76215 

386.27631 126.19348 75.52310 

366.95505 125.54653 81.25018 

\ 347.48105 124.92092 116.73838 

327.70676 124.48975 90.60525 

312.65046 124.39213 91.4E.93a ~02.52DC3 124.46083 90.&6081 

294.87521 124.61199 119.52314 

239.75702 124.t.1"0S 87.73437 

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346.29927 126.DllO 76.07527 

366.31159 126.05719 76.72958 

386.27681 126.19348 75.52310 

J 384;64442 149.22915 n.28404 

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347.26877 148.00317 89.13696 

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313.71316 147.4937(. 93.64661 

303.95355 147.55997 93.06032 

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291. 65773 147.9(1022 90.04832 

289.28503 148.11HOll 87.56196 .... 291. 75596 148.46134 85.08101 

296.44843 148.65755 !13.34406 .1 303.47860 148.85168 81.62554 

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P 346.13025 149.16906 78.81601 

365.41002 149.09785 79.44636 

384.64442 149.22915 78.28404 

3&3.01202 172.26482 81. 04499 

365.10481 171.66523 86.~5279 

347.05650 171.0:1542 91.411554 

328.72989 170.68582 95.02297 

314.77586 170.59535 95.82384 

305.38707 170.65906 95.25983 

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291.27589 171.25657 89.9703) 

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379.74723 218.33616 86.56688 

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I 303.44201 240.07979 100. H551 

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297.24MS 240.48305 97.19566 

299.343811 240.72071 95.09177 

I 303.32317 240.1l8710 93.61880 

! 309.28487 241.05173 92.16147 

I 317.25060 241.20273 90.82474 

329.26397 241.32224 89.76679 \ 345.45418 241.32087 89.77894 

361.80375 241.26048 90.31349 

378.11484 241.37183 89.32783 

376.48244 264.40750 92.08877 

361.40432 263.90263 96.55802 

346.20739 263.41443 100.87986 

330.77613 263.07796 103.85643 

319.02664 263.00178 104.53277 

311.12115 263.05543 104.05786 

305.15537 263.17335 103.01399 

301.16129 263.331Q3 101.61808 ... ' 299.23935 263.55854 99.60408 .-:. 301.24085 263.78555 97.59446 

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" 329.82037 264.36013 92.50&07 

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360.90218 264.30114 93.03023 

I 376.48244 264.40750 n.08877 I 17.0 10.0 / 

.f 391.17 -57.09 67.24 t, 369.02 -56.94 68.58 

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" 297.67 -56.65 71. 09 

289.57 -56.43 73.07 

284.17 -56.20 75.07 

281. 32 -55.88 77,93 

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289.74 

298.22 

309.46 

326.17 

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369.73 

391.17 

389.54 

368.11 

346.64 

325.37 

309.59 

299.12 

291.''} 

286.06 

283.31 

285.96 

291.45 

299.65 

310.53 

326.68 

347.91 

368.tn 

389.54 

387.91 

367.21 

346.47 

325.93 

310.68 

300.58 

293.01 

287.96 

285.30 

287.86 

293.16 

301. 09 

311.59 

327.20 

347.69 

367.80 

387.91 

386.28 

366.31 

346.30 

326.48 

311.78 

302.03 

294.73 

289.86 

287.29 

289.76 

294.M 

302.52 

312.65 

327.71 

347.48 

366.96 

386.28 

384.64 

-55.56 

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-79.98 

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-79.90 

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-78.64 

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82.09 

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303.43 -148.85 81.63 .... 296.45 -14lL66 83.34 : 1'-- 291.76 -148.46 85.08 /1 

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347.27 -148.00 89.14 

366.03 -14&.61 83.80 

384.64 -149.23 73.28 

,/ 383.01 -172.26 81. 04 

364.51 -172.14 82.16 / 345.96 -172.21 81. 56 

327.59 -172.21 81.54 

313.97 -172.'17 82.74 

304.93 -171.90 84.26 

298.17 -171.71 8~. ?l 

293.65 -171.53 87.58 .- 291. 28 -171.26 89.97 

293.56 -170.99 92.36 

f -~ / 298.30 -170.aO 94.02 

305.39 -170.66 95.26 

314.78 -170,60 95.S2 

328.73 -170.69 95.02 

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365.10 -171. 67 86.35 

383.01 -172.26 81. 04 , 3el. 38 -195.30 83.&1 

363.61 -195.18 84.88 

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328.15 -195.25 84.28 / 315.06 '·195.12 lI5.44 / 

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299.89 -194.77 88.48 j- 295.55 -194.59 fiO.D9 

293.27 -194.33 92.38 

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300.02 -193.89 96.27 

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315.84 -193.70 9/1.00 

329.24 -193.78 97.23 

346.84 -194.17 93.83 

364.18 -194.72 81L 90 

381. 38 -195 • .50 83.81 

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362.71 -218.22 87.60 

345.62 -218.28 87.04 

32!L 71 -2:'.8.28 87.03 

316.16 -21:1.16 8/1.13 

301.S3 -218.00 8'1.53 

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297.45 -217.66 92.59 

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X'R '.2U O.SIl 0.H2 1.42S •• U] 1.~44 '.605 1.6" 1.727 '.717 1.140 '.tOI •. U. 

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15.0 -1.0'452 -0.01517 -'.02797 -1.02241 -0.0181' -0.01471 -0.01191 -0.00'67 -1.00779 -1.00621 -1.0'411 -0.00160 -0.00~56 

SD.D -1.02110 - •. 01144 -1.011" -1.010a6 -1.ooa21 -0.Q0602 -0.004S6 -1.10117 -0.DD2S5 -0.00181 -1.GDI42 -0.10115 -0.00095 

'5.' -0.010'6 -'.0'801 -0.005" -0.00181 -0.0021] -0.00206 -0.00110 -D.~0141 -O.OOISO -1.00115 -0.00101 -o.cooa~ -0.00076 

60.1 -0.00\'8 -0.002a2 -1.OQI\l -O.oooal -0.00072 -0.00011 -0.00010 -0.G0061 -0.00062 -1.00056 -0.00049 -0.00042 -O.OCO]l 

15.0 -0.00136 D.COOIS 0.00070 0.00065 0.0000 1.00024 0.00011 0.00004 1.00000 -a.oooOI -0.00G02 -0.00002 -0.00002 

90.0 O. GO 124 0.00221 0.00236 0.G020S 0.GDU4 O.GOIlO 0.00104 0.00014 5.00061 0.0005~ 1.00041 G.OOO39 O.OOOll .::) ,.., \D~. 0 0.00311 0.OH6! O.OOHa 0.00'026 0.00H9 1.00Sot 0.00251 0.00206 0.00\67 '.00137 0.OCl12 0.00091 0.00015 

120.0 I.OC6H 0.'~8H 0.00920 o.OOUa O.Doa04 1.00665 O.OO~lS 0.OC~21 1.00352 1.00265 ·'.OOZll 0.00173 0.00H2 

135.0 0.D1I21 1.01405 0.01606 0.01610 0.01412 0.01215 0.00959 O.OOHI 0.00534 0.00H3 0.00169 0.002911 0.002U -' 

150.0 O.cta01 0.02125 0.02255 0.02221 O.UOIO 0.01130 0.01451 0.01204 1.00U9 O.OCSIC 0.0C651 1.005S2 1.00431 r': .~ 165.0 1.03179 •. DHO~ O.OHot 0.IS205 1.028U O. 02611 I. a 246 ~ 0.02231 '.0\9211 0.0\609 '.0\ lOS 1.01015 '.0 Oal ~ " laG.O 1.0lSH •• DUal O.OHH 1.0\252 O.OHU 0.01514 0.OH20 0.OS\65 1.027H 0.02293 I.DlSU I.OIH2 0.01111 

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~~ , 255.0 1.00410 0.00461 O.OOUI 0.00417 O.OOHO O.OalOI 0.0024S 0.002DS 1.001" O.OOIH O.OOIlS O.OOOH 0.00079 ~10.0 o .OOIH I.HZ09 O.OOZIS 0.001&8 0.00\56 0.00127 0.D0102 O.OOOU O.ICOU O.OOC56 I.OODH o.IOGH O.OOOll 

~t; i 285.0 -0.00146 -0.00019 O.OOOSO 0.00035 0.00024 0.0001l 0.0~006 0.00001 -0.'0002 -o.oooas -O.OOOOS -1.00001 -0.0000] 

lOO.O -0.C051~ -0.00SI9 -0.001'6 -O.OOISS -O.OOIOS -0.00092 -0.00082 -0.00014 -0.000" -0.0005a -O.OOO~I -O.OOQ\~ -0.000l8 

\~ :1 ]I~.O -0.01082 -o.ooala -i.G059' -0.00\29 -O.OOSII -0.002\5 -0.00191 -0.0016S -,.oOl~a -0.00121 -0.0010' -0.000'0 -0.00077 

"}<1 lla.O -0.02106 -0.01116 -0.0IS65 -0.01061 -o.ooal~ -'.00614 -0.00~'2 -O.OOS\' -0.00261 -0.00209 -'.O~I" -1.0011] -O.OOIOS 

,I I ]45.1 -0.142~] -0.01111 -0.02671 -0.021\2 -0.01110 -0.01]'9 -0.0113~ -0.00919 -1.001~2 -0.00595 -'.10"7 -0.00357 -0.0026~ 

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15. a a.C0l2Z O.OOZH 0.'0024 -1.00125 -0.00200 -0.00225 -0.00Z20 -1.00195 -0.00157 -O.COIIS -0.0007] -0.00018 -0.00012 

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120.0 O. OI~B 0.OH15 O. GIHI '.011.7 I.UalO I. DU71 0.005U •• OOH~ 1.0~lU O.tD255 '.OC205 '.00167 O.OOIH 

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150.0 0.02711 0.02900 '.02115 0.02296 '.OIH2 O.OHH 0.01121 '.OUlI '.DDUS 0.10522 e.1040& '.00H7 O.@c2~a 

\6S.0 0.CH21 O.O~S" C.Ol!!H O.IB46 1.13014 O.027U '.02257 0.01797 0.0115' '.01011 I.ODIH '.COSH '.00.0} 

160.0 0.05955 O. 0"2' 0.05335 O.GH" 0.0.501 '.0.191 '.OJ532 '.02757 0.120US a.DlU7 '.OID •• 0.00130 0.C0519 

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210.0 O. G2736 0.02816 0.026U '.02207 0.C17OS 1.IHIl 0.01101 '.00&63 0.00671 •• a a 524 0.00"09 '.aOJ2Z 0.C0255 

225.0 0.01971 0.02101 I.Dl970 •. 01627 0.01252 I.OOHO O.~QJ~~ '.OOH2 '.00H2 0.0013\ C. 00267 0.00216 0.00\16 

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285.' 0.002H 0.00156 O.COOOl -I.GOIII -0.OOI5~ -'.O~16' -0.00119 -0.0015' -1.00125 -0.00091 -0.00061 -0.00015 -O.OCOI' 

100.0 -0.OC22~ -1.0021' -0.00117 -1.00.21 -O.00~14 -0.00~1' -I.OG~'I -1.001.6 -'.00121 -1.0025' -0.001" -0.00141 -0.00097 

115.0 -0.00512 -0.0069' -0.00611 -0.006~' -'.00616 -1.00.112 -0.00552 -0.00531 -'.00"5 -O.OO~O] -'.DOl17 -1.00216 -0.00220 

JJO.O -0.01!1! -'.015~1 -0.01222 -0.0~'5' -0.OD16' -O.DO'." -0.00510 -1.00525 -0.00491 -1.104'0 -1.00426 -0.00391 -0.00356 

3'5.0 -0.01562 -0.02815 -0.02130 -0.018'1 -0.0151' -O.Oll" -'.109,a -0.001;' -1.00'10 -'.CO"S -i.101'3 -0.1025' - •• 002Q~ 

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APPENDIX C 

Supplementary Load3 Analysis Comparisons 

To supplement the loads analysis results shown in Figures 8-6 

through 8-41, this appendix contains several additional compar- isons in tabular form. 

207 

.: . 
/. 

, ----

/ 

.----- , 

\ 

, \ 

I 

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i 

, 

, . 

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Flight Velocity - Knots 112.5 162.5 

l/DE (without upwash) 7.80 8.21 

l/OE (with upwash) 7.91 8.53 

PlL Amplitude-lbs (without upwash) 305 929 

PlL Amplitude-lbs (with upwash) 435 1014 

Vertical Shear Amplitude-lbs (without upwash) 1897 3476 

Vertical Shear Amplitude-lbs (with upwash) 1410 4106 

FZF-lbs (without upwash) 1182 1686 

FZF-lbs (with upwash) 1219 1557 

Flight Condition 3 4 

Variation of Equivalent Lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch link Lead Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Flight Velocity from loads Analysis. Rotor lift, Gross 

Weight, and Rotor Radius Are Held Constant. 

208 

/ .I \ 
I 

I 

" 

/ 

Flight Velocity - Knots 112.5 162.5 

L/DE (without upwash) 7.45 7.29 

L/DE (with upwash) 7.26 7.65 

PLL Amplitude-lbs (without upwash) 407 735 

PLL Amplitude-lbs (with upwash) 546 927 

Vertical Shear Amplitude-lbs (without upwash) 5386 3306 

Vertical Shear Amplitude-lbs (with upwash) 5220 4694 

FZF-l bs (without uDwash) 1733 2685 

FZF-lbs (with upwash) 1594 2444 

Flight Condition 9 10 

Variation of Equ~valent Lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link Load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Flight Velocity from Loads Analysis. Rotor Lift, Wing Lift, Gross ~eight, Flat Plate Area for Auxiliary Thrust, and Rotor Radius Are 

field Constant. 

209 

, 
~ 

. ,~ 

Flight Velocity - Knots 112.5 162.5 

L/DE (without upwash) 6.96 8.94 

L/DE (with upwash) 7.10 9.06 

PLL Amplitude-lbs (without ur.oJash) 551 1019 

PLL Amplitude-lbs (with upwash) 519 1044 

Vertical Shear Amplitude-lbs (without upwash) 1102 2270 

Vertical Shear Amplitude-lbs (with upw~sh) 1288 2815 

FZF-lbs (without upwash) 682 1223 

FZ!=-lbs (with upwash) 706 1005 

Flight Condition 11 12 

Variation of Equivalent Lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link Load Vibratory Amplitude, and Vertical Hub Force FOIJrth 

Harmonic Amplitude with Flight Velocity from LQads AnalysiS. Rotor Lift, Gross 

Weight, and Rotor Radius Are Held Constant . 

210 
~ 

.,--

· . 

Flight Velocity - Knots 112.5 162.5 

l/OE (without upwash) 7.23 8.06 

L/OE (with upwash) 7.66 8.99 

PLL Amplitude-lbs (without upwash) 321 825 

PLL Arnplitude-lbs (with upwash) 485 1154 

Vertical Sh~ar Arnplitude-lbs (without upwash) 1449 2598 

Vertical Shear Amplitude-lbs (with upwash) 1912 3449 

FZF-lbs (without upwash) 754 1446 

FZF-lbs (with upwash) 682 1503 

Flight Condition 13 14 

Variation of Equivalent Lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link Load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Flight Velocity from Loads Analysis. Rotor Lift, Gross 

Weight, Flat Plate Area for Auxiliary Thrust, and Rotor Radius Are Held Constant. 

211 
Flight Velocity - Knots 112.5 162.5 

LIDE (without upwash) 7.09 8.93 

LIDE (with upwash) 6.63 8.72 

Pll Amplitude-lbs (without upwash) 483 1025 

PLL Amplitude-lbs (with upwash) 532 1052 

Vertical Shear Amplitude-lbs (without upwash) 897 2556 

Vertical Shear Amplitude-lbs (with upwash) 1431 3436 

FZF-lbs (without upwash) 720 1362 

FZF-lbs (with upwash) 795 1194 

Flight Condition 15 16 

Variation of Equivalent Lift-to-Orag Ratio, rlap Hinge Vertica1 Shear Vibratory Af'I'~litude, Pitch Link load Vibratory Amplitude, and Vertical Hub Force Fourth 

t,o- ~onic Amplitude with Flight Velocity from loads Analysis. ~otor lift, Wing Lift, Gross Weight, and Rotor Radius Are Held Constant. 

212 
~ -

'\ 

,--

. ~ 

.-. 

Flight Velocity - Knots 112.5 162.5 

UOE (without upwash) 7.27 8.04 

L/DE (with upwash) 7.18 8.57 

PLL Amplitude-lbs (without upwash) 261 869 

PLL Amplitude-lbs (with upwash) 429 905 

Vertical Shear Amplitude-lbs (without upwash) 3124 3234 

Vertical Shear Amplitude-lbs (with upwash) 3138 4630 

FZF-lbs (with::Jut upwash) 765 1559 

FZF-lbs (with upwash) 655 1521 

Flight Conditio~ 17 18 

Variation of Equivalent Lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link Load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with F'light Velocity from Loads Analysis. Rotor Lift, Wing Lift, Gross Weight, Flat Plate Area for Auxiliary Thrust, and Rotor Radius Are 

Held Constant . 

213 

.... ----- .-.. -.. . ---------,,-01"' 
. / ~/' 

,--

I 

Tcosa/nR2-psf 6.48 9.34 

L/DE (without upwash) 7.80 7.21 

L/DE (with upwash) 7.91 7.38 

PLL Anplitude-lbs (without upwash) 305 756 

PLL Amplitude-lbs (\oJi th upwas h) 435 776 

Vertical Shear Arnplitude-lbs (without upwash) 1897 2270 

Vertical Shear Amplitude-lbs (with upwash) 1410 2360 

FZF-lbs (without upwash) 1182 1253 

FZF-lbs (with upwash) 1219 1344 

Flight Condition 3 1 

Variation of Equivalent Lift-to-Orag Ratio, Flap HingQ Vertical Shea,' Vibratory Amplitude, Pitch Link Load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Vertical Component of Disk Loading from Loads Analysis. Flight Velocity and Rotor Radius Are Held Constant. 

214 

t 

• 
... 

~. ;. .. 

~ 

.- .- .-- . -----..... -.. ~ ... -

lift-lbs 0 S066.7 

L/DE (without upwash) 7.S0 7.S3 

L/DE (with upwash) 7.91 7.30 

PLL Amplitude-lbs (without upwash) 305 293 

PLL Amplitude-lbs (with upwash) 435 493 

Vertical Shear Amplitude-lbs (without upwash) lS97 2336 

Vertical Shear Amplitude-lbs (with upwash) 1410 lS20 

FZF-lbs (~ithout upwash) 1182 1173 

FZF-lbs (with upwash) 1219 1386 

Flight Condition 3 5 

Variation of Equivalent Lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link Load Vibratory Amplituda, and Vertical Hub Force Fourth 

Harmonic Amplitude with Wing Lift from Loads Analysis. Rotor Lift, Flight Velocity, and Rotor Radius Are Held Constant. 

215 
, 

",--

. ', 

I ' 

~. 

Lift-lbs 0 8066.7 

l/DE (without upwash) 6.96 7.09 

L/DE (with upwash) 7.10 6.63 

PlL Amplitude-lbs (without upwash) 551 483 

PLL Amplitude-lbs (with upwash) 519 532 

Vertical Shear Amplitude-lbs (without upwash) 1102 897 

Vertical Shear Amplitude-lbs (with upwash) 1288 1431 

FZF-lbs (without upwash) 682 720 

FZF-lbs (with upwash) 706 795 

Flight Condition 11 15 

Variation of Equivalent Lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link Load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Wing lift from Loads Analysis. Rotor Lift, Flight Velocity, and ~otor Radius Are Held Constant . 

216 
,,-

... 

'. 

., 

\. 

.. 

I 

\ 

Li ft-l bs 0 8066.7 

LIDE (without upwash) 8.94 8.93 

L/DE (with upwash) 9.06 8.72 

PLL Amplitude-lbs (without upwash) 1019 1025 

PLL Amplitude-lbs (with upwash) 1044 1052 

Vertical Shear Amplitude-lbs (without upwash) 2270 2556 

Vertical Shear Amplitude-lbs (with upwash) 2815 3436 

FZF-lbs (without upwash) 1223 1362 

FZF-lbs (with upwash) 1005 1194 

Flight Condition 12 16 

Variation of Equivalent lift-to-Drag Ratio, Flap Hinge Vertical Shaar Vibratory Amplitude, Pitch Link Load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Wing Lift from loads Analysis. Rotor Lift, Flight Yelocity, and Rotor Radius Are Held Constant . 

217 
"/ . r 

I 

Variation of Equivalent Llft-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link Load Vibratory Amplitude, and Vertic~1 Hub Force Fourth 

Harmonic Amplitude with Wing Lift from Loads Analysis. Rotor Lift, Flight Velocity, Flat Plate Area for Auxiliary Thrust, and Rotor Radius Are Held Constant. 

218 
( . 

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, 

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.' 

" 

/ 

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" / 

Uft-lbs 0 4033.3 8066.7 

l/OE (without upwash) 7.40 7.34 7.29 

LlOE (with upwash) 8.14 7.80 7.65 

PLL Amplitude-lbs (without upwash) 734 688 735 

PlL Amplitude-lbs (with upwash) 916 882 927 

Vertical Shear Amplitude-lbs (without upwash) 3766 3873 3306 

Vertical Shear Amplitude-lbs (with upwash) 4359 4830 4694 

FZF-lbs (without upwash) 2736 2693 2685 

FZF-lbs (with upwash) 2507 2402 2444 

Flight Condition 8 21 10 

Variation of Equivalent Lift-to-Orag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Wing Lift from Load5 Analysis. Rotor Lift, Flight Velocity, Flat Pla.te Area for Auxiliary Thrl!st, and Rotor Radius Are Held Constant . 

219 

/. . / 
i. . ~ 

/ 

"\ 

, i : I ;.' 

. . .' ' 

/ ,.. 

Variation of Equivalent lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch link load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Wing lift from loads Analysis. Rotor lift, Flight Velocity, Flat Plate Area for Auxiliary Thrust, and Rotor Radius Arc Held Constant. 

220 

-' / 1 

! ' 

I 

i 

! , 

1 

I 

l 

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t 

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f ", 

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! 

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fe-sq ft 0 22.9 

L/DE (without upwash) 7.80 7.44 

L/DE (with upwash) 7.91 7.85 

PLL Amplitude-lbs (wi thout upv/ash) 305 419 

PLL Amplitude-lbs (with upwash) 435 460 

Vertical Shear Amplitude-lbs (without upwash) 1897 2905 

Vertical Shear Amplitude-lbs (with upwash) 1410 2877 

FZF-lbs (without upwash) 1182 1629 

FZF-l bs (with upwash) 1219 1561 

Flight Condition 3 7 

Variation of Equivalent lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Flat Plato Area for Auxiliary Thrust from Loads Analy- sis. Rotor Radius, Rotor Lfft, Gross Weight. and Flight Velocity Are Held 

Constant. 

222 

, ! 
/ •. 

! 

I ./ 

I 

, 

, 

/ 

fe-sq ft 0 22.9 

L/DE (without upwash) 6.96 7.23 

LIDE (with upwash) 7.10 7.66 

PlL Amplitude-lbs (without upwash) 551 321 

Pll Amplitude-lbs (with upwash) 519 485 

Vertical Shear Amplitude-lbs (without upwash) 1102 1449 

Vertical Shear Amplitude-lbs (with upwash) 1288 1912 

FZF-lbs (without upwash) 682 754-

FZF-lbs (with upwash) 706 682 

Flight Condition 11 13 

Variation of Equivalent Uft-to-Drag Ratio, Flap Hinge Vertical Shear Vibt'atory Amplitude, Pitch link Load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitud~ with Flat Plate Area for Auxiliary Thrust from Loads Analy- sis. Rotor Radius, Rotor Lift, Gross Weight, and Flight Velocity Are Held 

Constant. 

. 223 

, 
./ 

/ / 

, 

., 

/ 

/ 

... 

fe-sq ft 0 22.9 

l/DE (withcut upwash) 8.94 8.06 

L/DE (with upwash) 9.06 8.99 

PLl ~mplitude-lbs (without upwash) 1019 825 

PLL Amplitude-lbs (with upwash) 1044 1154 

Vertical Shear Amplitude-lbs (without upw:tsh) 2270 2598 

Vertical Shear Amplitude-lbs (with upwash) 2815 3449 

FZF-lbs (w:thout upwash) 1223 1446 

FZF-lbs (with upwash) 1005 1503 

Flight Condition 12 14 

Variation of Equiva',ent Lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link Loa~ Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Flat Plate Area for Auxiliary Thrust from Loads Analy- $is. Rotor Lift, Gross Weight, Flight Velocity, and Rotor Radius Are Held 

Constant. 

224 
'. " I 

/ 

, 

I 

! 

I 

I 

I 

I 

I 

,-

- ::---:: 

'. 

.. -- -----:-

-, 

'- '/' '-...... - ... -........ -~-. 

! , 

I, 

I 1. 

fe-sq ft 0 22.9 

l/OE (without upwash) 7.83 7.45 

LlOE (with upwash) 7.30 7.26 

PLl Amplitude-lbs (without upwash) 293 407 

PLl AIIIP 1 i tude-l bs (with upwash) 493 546 

Vertical Shear Amplitude-lbs (without upwash) 2336 5386 

Vertical Shear Amplitude-lbs (with upwash) 1820 5220 

FZF-lbs (without upwash) 1173 1:733 

FZF-lbs (with upwash) 1386 1594 

Fli ght Condi t ion 5 9 

Variation of Equivalent Lift-to-Drag ~atio, Fla~ Hinge Vertical Shear Vibratory Amplitude, Pitch Link Load Vi~ratory Amplitude, and Vertical Hub ~~rce Fourth 

Harmonic Amplitude with Flat Plate Area for Auxiliary Thrust from Loads Analy- sis. Rotor Lift, Gross Weight, Flight Velocity, ~ing Lift, and Rotor Radius 

Are Held Constant. 

225 
,--, 

" 

---," 

fe-sq ft 

L/DE (without upwash) 

UDE (\~ith upwash) 

" ' 

PLL '~plitude-lbs (without upwash) 

PLL Amplitude-lbs (with upwash) 

Vertical Shear Amplitude-lbs (without up~ash) 

Vertical Shear Amplitude-lbs (with upwash) 

FZF-lbs (without upwash) 

FZF-1bs (with upwash) 

Flight Condition 

o 

7.09 

6.63 

483 

532 

897 

1431 

720 

795 

15 

'~:', , 

22.9 

7.27 

1.18 

261 

429 

3124 

3138 

765 

655 

17 

Variation of Equivalent Lift-to-Orag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link Load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Flat Plate Area for Auxiliary Thrust from Loads Analy- sis. Rotor Lift, Gross Weight, Flight Velocity, Wing Lift, and Rotor Radius 

Are Held Constant. 

226 
!~-

-_._ ...... ....-. ..... , .. , ''- .).. .............. ~ .. 

fe-sq ft 0 22.9 

L/DE (without upwash) 8.93 8.04 

L/OE (with upwash) 8.72 8.57 

PLL Amplitude-lbs (without upwash) 1025 869 

PLL Amplitude-lbs (with upwash) 1052 905 

Vertical Shear Amplitude-lbs (without upwash) ·2556 3234 

Vertical Shear Amplitude-lbs (with upwash) 3436 4630 

FZF-lbs (without upwash) 1362 1559 

FZF-lbs (with upwash) 1194 1521 

Flight Condition 16 18 

Variation of Equivalent Lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory A~pl itude, Pitch Link Load Vibratory Ampl itl,de, and Vertical Hub Force Fourth 

Harmonic Amplitude with Flat Plate Area for Auxiliary Thrust from Leads Analy- sis. Rotor lift, Gross Weight, Flight Velocity, Wing lift, a~d Rotor Radius 

Are Held Constant. 

227 
,I 

I 

.I 

" ; 

.. ..-

.~ 

I 

---- . 

/ 

" 

,., .. 

fe-sq ft 0 22.9 

Lift-lbs 0 8066.7 

L/OE (without upwash) 7.80 7.45 

L/OE (with upwash) 7.91 7.26 

PLL Amplitude-lbs (without upwa5h) 305 407 

PLL Amplitude-lbs (with up\:lash) 435 546 

Vertical Shear Amplitude-lbs (without upwash) 1897 53136 

Vertical Shear Amplitude-lbs (with upwash) 1410 5220 

FZF-lbs (without upwash) 1182 1733 

FZF-lbs (with upwash) 1219 1594 

Flight Condition 3 9 

Variation of Equivalent Lift-to-Orag Ratio, Flap Hinge Vertical Shear Vibratory Ampl it'Jd~, Pitch Link Load Vibratory .'\rnpl itude, and Vertical Hub Force Fourth 

Harr.;c:,ic Ampl it .. ce with F1<lt P1Jte Area for Auxi 1 iary Thrust and Wing Lift from 

Loads Analysis. Rot.)r Lift. F1iCjht Velocity, dnU Rotor Ra~ius fij'e Held Const-lnt. 

228 

! 

; 

; 
-/ .. 

.< , 

--------;;:-

,/ ..... 

/, 

< ,-

/ . 

/ 

~",.-'-" 

,/j 

,. 

fe-sq ft 0 22.9 

lift-lbs 0 8066.7 

L/DE (without upwash) 6.96 7.27 

L/DE (with upwash) 7.10 7.18 

PLL Amplitude-lbs (without upwash) 551 261 

PLL Amplitude-lbs (with upwash) 519 429 

Vertical Shear Amplitude-lbs (without upwash) 1102 3124 

Vertical Shear Amplitude-lbs (with up\>/ash) 1288 3138 

FZF-lbs (without upwash) 682 765 

FZF-lbs (with upwash) 706 655 

Flight Condition 11 17 

Variation of Equivalent Lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link Load Vibratory Ar,'plitude, and Vertical Hub Force Fourth 

Harmonic Amplitude 'tlith Flat Plate Area for Auxiliary Thrust from Loads Analy- sis. Rotor Lift, Flight Velocity, and Rotor Radius Are Held Constant. 

229 

----- < ; <~-----

«-< (', .. t. ,', 
,. 

" 

.. 

.- ---

" . , / 

\ 

fe-sq ft 0 22.9 

Lift-lbs 0 8066.7 

L/DE (without upwash) 8.94 8.04 

L/DE (with upwash) 9.06 8.57 

~LL Amplitude-lbs (without upwash) 1019 869 

PLL Amplitudc-lbs (with upwash) 1044 905 

Vertical Shear Amplitude-lbs (without upwash) 2270 3234 

Vertical Shear Amplitude-lbs (with upwash) 2815 4630 

FZF-lbs (\'iithout upwJsh) 1223 1559 

FZF-lbs (with upwash) 1005 1521 

Fl ight Condition 12 18 

Variation of Equivalent Lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link Load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Flat Plate Area for Auxiliary Thrust from Loads Analy- sis. Rotor Lift, Flight Velocity, and Rotor Hadius Are Held Constant. 

230 

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J 

t 

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, 
. 

" 

) 

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././ 

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! i. 1,'" 

f /" . / 

I· 

, 

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I 

j. .• 

,i 

, ' ' 

Rotor Radius-ft 25 30 

LICE (without upwash) 6.96 7.21 

LIDE (with upwash) 7.10 7.38 

PLL Amplitude-lbs (without upwash) 551 756 

PLL Amplitude-lbs (with upwash) 519 776 

Vertical Shear Amplitude-lbs (without upwash) 1102 2270 

Vertical Shear Amplitude-lbs (with upwash) 1288 2360 

FZF-lbs (without upwash) 682 1253 

FZF-lbs (with upwash) 706 1344 

FHght Condition 11 1 

Variation of Equivalent Lift-to-Orag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link Load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Rotor Radius from Loads Analysis. Flight Velocity and 

Oisk Loading Are Held Constant. 

231 

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" 

.,~ 
l,. / 

,i',/ II 

, \ , I,' ~ II 

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f 

I 

I. 

I 

/ ' I ,,' 

1'.1" . 

, :" 

" 

! 

.. \ 

... 

..... ; .' 

/ 

Rotor Radius-ft 25 30 

L/OE (without upwash) 6.96 7.80 

LICE (with upwash) 7.10 7.91 

PLL Amplitude-lbs (without up\~ash) 551 305 

PLL Amplitude-lbs (with upv/ash) 519 435 

Vertical Shear Amplitude-lbs (without upwash) 1102 1897 

Vertical Shear Amplitude-lbs (with upwash) 1288 1410 

FZF-lbs (without upwa~h) 682 1182 

FZF-lbs (with upwash) 706 1219 

Flight Condition 11 3 

Variation of Equivalent Lift-to-Orag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link Load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Rotor Radius from Loads Analysis. Flight Velocity, Rotor Lift, and Gross Weight Are Held Constant. 

232 

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; 

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f.~ " , . , , "';"// '.' , ,I _ -' 

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t, / '. 

/~ 

/ 

! I , " " , 

Rotor Radius-ft 25 30 

llDE (without upwash) 8.94 8.21 

llDE (with upwash) 9.06 8.53 

Pll Amplitude-lbs (without upwash) 1019 929 

Pll Amplitude-lbs (with upwash) 1044 1014 

Vertical Shear Amplitude-lbs (without upwash) 2270 3476 

Vertical Shear Amplitude-lbs (with upwash) 2815 4106 

FZF-lbs (without upl~ash) 1223 1686 

FZF-lbs (with upwash) 1005 1557 

Flight Condition 12 4 

Variation of Equivalent lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch link load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplituda with Rotor Radius from loads Analysis. Flight Velocity, Rotor lift, and Gross Weight Are Held Constant. 

233 

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! 

l . 

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,. 

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I 

.~ ---_.-

./ / 

;. 

Rotor Radius-ft 25 30 

L/DE (without upwash) 7.23 7.44 

L/DE (with upwash) 7.66 7.85 

PLL Amplitude-lbs (without upwash) 321 419 

PLL Amplitude-lbs (with upwash) 485 460 

Vertical Shear Arnplitude-lbs (without upwash) 1449 2905 

Vertical Shear Amplitude-lbs (with upwash) 1912 2877 

FZF-lbs (without upwash) 754 . 1629 

FZF-lbs (with upwash) 682 1561 

Flight Condition 13 7 

Variation of Equivalent Lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link Load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Rotor Radius from Loads Analysis. Flight Velocity, Rotor Lift, Gross Height, and Flat Plate Area for Auxiliary Thrust Are Held 

Constant. 

234 

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/ 

I 

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{-

/ 

ji 
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I 

Rotor Radius-ft 25 30 

L/DE (without upwash) 8.06 7.40 

L/DE (with upwash) 8.99 8.14 

PLL Amplitude-lbs (witho;;t up\'iash) 825 734 

PLL Amplitude-lbs (with upwash) 1154 916 

Vertical Shear Amplitude-lbs (without upwash) 2598 3766 

Vertical Shear Amplitude-lbs (with upwash) 3449 4359 

FZF-lbs (without upwash) 1446 2736 

FZF-lbs (with upwash) 1503 2507 

Flight Condition 14 '8 

Variation of Equivalent Lift-to-Orag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link Load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Rotor Radius from Loads Analysis. Flight Velocity, Rotor Lift, Gross Height, and Flat Plate Area for Auxiliary Thrust Are Held 

Constant. 

235 

.I \ ) 
/ 

" , ~. 

/' 

,.' 

.' 

. I 

/ 

/,. 

.. ' / 

I 

, '. 

.... 

1.~~- ... -- " 

... :.~" 

Rotor Radius-ft 25 30 

L/DE (without up~ash) 7.09 7.83 

llDE (with upwash) 6.63 7.30 

PLL AWoplituda-lbs (without upwash) 483 293 

PLL Amplitude-lbs (with upwash) 532 493 

Vertical Shear Amplitude-lbs (without up~ash) 897 2336 

Verticill SheJr Arnplitude-lbs (with upwash) 1431 1820 

FZF-lbs (without upwash) 720 1173 

FZF-lbs (with upwash) 795 1386 

Flight Co~dition lS 5 

Variation of Equivalent lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link load Vibrat~ry Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Rotor Radius from loads Analysis. Flight Velocity. Rotor lift, Wing Lift. and Gross Weight Are Held Constant. 

236 

.' 
/ 

f 

• '. I 

,.' \ ' 

Rotor Radius-ft 25 30 

L/DE (without upwash) 8.93 8.21 

L/DE (with upwash) 8.72 8.01 

PLL ~~plitude-lbs (without upwash) 1025 873 

PLL Amplitude-lbs (with upwash) 1052 987 

Vertical Shear Arnplitude-lbs (without upwash) 2556 3431 

Vertical Shear Amplitude-lbs (with upwash) 3436 3188 

FZF-lbs (without upwash) 1362 1730 

FZF-lbs (with upwash) 1194 1795 

Flight Condition 16 6 

Variation of Equivalent Lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibruto~ 

Amplitude, Pitch Link Load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Rotor Radius from Loads Analysis. Flight Velocity, Rotor Lift, Wing Lift, and Gross Weight Are Held Constant . 

237 

-._.---_._-_ ... ", . ' .. -.. ------- '.'~ ~-:-- .. --.-- -reg 

\ 

;~ 
" \ 

\. 

'-

Rotor Radius-ft 25 30 

l/OE (without upwash) 7.27 7.45 

l/OE (with upwash) 7.18 7.26 

Pll Amplitud~-lbs (\,/i thout up\tash) 251 407 

Pll Amplitude-lbs (with upwash) 429 546 

Vertical S~ear Amplitude-lbs (without upwash) 3124 5386 

Vertical Shear Amplitu~e-lbs (with upw ... <;h) 3138 5220 

FZF-lbs (without upwash) 76~ 1733 

FZF-lbs (with upwash) 655 1594 

Flight Condition 17 9 

Variation of Equivalent Lift-to-Drag Ratio, Flap HingE Vertical Shear Vibratory Amplitude, Pitch Link Loac Vibratory Amplitude, and 'Jertical Hub Force Fourth 

Harmonic Amplitude with Rotor Radius fror:! Loads Analysis. Flight Velocity. Rotor Lift. Wing Lift, Gross ~'eight. and Fiat Plate Area fOI' Auxiliary Thl'lJs~ 

Are Held Constant. 

238 

,r 
. ~ 

\ 

'. 

--. 

~­

( 

",: ... 

-- .. ,--- . / 

l !. 

/ ., -

Rotor Radius-ft 25 30 

LIDE (without upwash) 8.04 7.29 

L/DE (with upwash) 8.57 7.65 

PLL Amplitude-lbs (without upwash) 369 735 

PLL Amplitude-lbs (with upwash) 905 927 

Vertical Shear Amplitude-lbs (without upwash) 3234 3306 

Vertical Shear Amplitude-lbs (with upwash) '4630 4694 

FZF-lbs (without upwas/l) 1559 2685 

FZF-lbs (with upwash) 1521 2444 

Flight Condition 18 10 

Variation of Equivalent Lift-to-Drag Ratio, Flap Hinge Vertical Shear Vibratory Amplitude, Pitch Link Load Vibratory Amplitude, and Vertical Hub Force Fourth 

Harmonic Amplitude with Rotor Radius from Loads Analysis. Flight Velocity, Rotor Lift, Wing Lift, Gross Weight, and Flat Plate Area for Auxiliary Thrust 

Are Held Constant . 

239 
~- ... -

APPENDIX D 

Surface Plots 

This appendix contains a few surface plots of upwash values, UP, the 

steady value and first ten harmonics of tha blade loading, and 

the same blade loading with the steady value and first two harmonics removed. The blade loading is from B-55. The upwash values in this appendix are not nondimensionalized by rotor tip speed. They have units of ft/sec. The blade loading is in 

lb/in. These surface plots are examples only. They show that 

the effects of fuselage/wing/engine upwash on blade loading distribution is not dramatic. 

240 

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ISOLATED ROTOR 

o r'c(:;·,~\'L'.l.~ P ;'. !:I:': • ~~ 

OF POOR QUi-\LI~ 

FUSELAGE UPWASH 

U~WAIIl vrLOCITV, HOIIUAL CO!l~ONINT, U~WAIIl veLOCITY, 1l0llUAL COU'OIlUIT, 

.oUII III' ... , 'U'fLAO. 

'LA Dr LO"DINC 11_,lft' 

HAII!lONICI 0 TO 10 

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Flight Condition 7 

243 

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I. Report No. I %. GQo,,;mmcs:nt ~ No. 3. Raci;:liant'l c:.taI09 No. 

CRiI 177349 

4. Tltte 11M Subtll1a Il. rl:l:=t Cam 

FUSELAGE UPWASH EFFECTS ON RSRA ROTOR SYSTEMS AU,Eust lC1Rr; 

C,\ f':11ornlirti O~C!'I Cccta 

7. Aumcr'" II. 1\':Ifurmi"l Or\;:nimcn Rcpcn No. 

J. COWlln, L. Dadone D2lo-l2359-1 

ta. \~mt: Unit t,!o. 

0. FWfcrll'lin; Ort;:ni=tl:ln f.:.:m. end ~ 

Booine V.rtol Co~nn1 11. Ccr.z';:t Of' Gn.nt Nol • 

P.O. Box 160S3 

PhilAdelphia, PA 19142 NAS2-11307 

11 T@lI of R c;IOR III\d P5'icd Covued 

1%. S;l::nr:)ri1l9 k;.zrcy tbne II\d ~ Coutractor Enporc 

National Aeronzutics ~ Sp~ca Administration 14. ~~ I.;mcy CcaI U.ahin3ton, D.C. 20546 

RTOP 505-42-51 

15. Soip;::lctNfturv Nota 

Point of ContAct: Jeffrey L. Cross, Ames Research Center. MoffedeField. CA 94035 

Phone II: (415) 694-/1571 FTS 464-6571 MIs 237-3 

18. Absna 

The effects of RSRA fuselage configurations on rotor performance and loads have been qUllntified llnalytically be means of currently available ;otential flow and rotor analysis . Four configurations of the Rotor S:'stems Research Aircraft .(RSRA) were considered ,in this 

study. They were: 

(1) Fuselage alone (conventional helicopter) 

(2) Fuselage with auxiliary propulsion 

(3) Fuselage with wings (auxiliary lift) 

(4) Fuselage with both auxiliary lift and propulsion 

The rotor system investigated was identical to a CH-47D front rotor except that it had fou 

instead of three blades. Two scaled-down versions of the same rotor were also analyzed 

to determine the effect of rotor scale on the fuselage upwash effects. 

The flight ccnditions considered for the upwash study are discussed. The potential flow. 

models for the RSRA configuration, with and without the wings and the auxiliary propulsion 

system, are presented. The results of fuselage/Wing/propulsion system upwash on performance and loads are also presented. 

The plethora of data resulting from this study reflected the existence of complicated flow 

interactions and did not lend itself to straightforward interpretation in all cases. More 

often than not though, neglecting fuselage upwash causes an underestimation of performance 

and an underestimation of loads. 

'7. K.., WcnI1 'S~ by Auttal!) I to. OiJlributilln StmmcnC 

Helicopter rotor UI1!.1m.1ted Interactional aerodynamics 

Compound helicopters 

Rotor performance Subject Category 02 RSRA 

teo Soxurity ~~I. 101 ttn ~I I ;0. ~tV O=:il. 101 ~ I%'ir.'I 121. Pl:». of p~ 122. PrietO 

Uncla:ullflcd UnclasclUed 2/14 

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End of Document