Low-speed stability and control characteristics of a transport model with aft-fuselage-mounted advanced turboprops

Document

NASA

Technical

Paper

c .a-

April 1986

Low-Speed Stability and

Control Characteristics of

a Transport Model With

Aft -Fuselage-Mounted

Advanced Turboprops

Zachary T. Applin

and Paul L. Coe, Jr.

NASA

Tech n i ca I

Paper

Low-Speed Stability and

Control Characteristics of

a Transport Model With

Aft -Fuselage-Moun t ed

Advanced Turboprops

Zachary T. Applin

and Paul L. Coe, Jr.

Langley Research Center

Hampton, Virginia

r u n s n

Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

I

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

Symbols . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

I

Model . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3

Tests and Corrections 3

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Presentation of Results . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 Disc:ission of Results . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 I I Aerodynamic Characteristics of Isolated Propeller and Nacelle . . . . . . . . . . . . . . . 4

Aerodynamic Characteristics of Advanced Turboprop Transport Model . . . . . . . . . . . 4

Effect of thrust on longitudinal aerodynamic performance . . . . . . . . . . . . . . . . 4

Horizontal tail aerodynamic characteristics . . . . . . . . . . . . . . . . . . . . . . 5

Effect of thrust in ground effect . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

I Effect of thrust on lateral-directional aerodynamic characteristics . . . . . . . . . . . . . 5

Rudder aerodynamic characteristics . . . . . . . . . . . . . . . . . . . . . . . . . 5

Engine-out characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

Summary of Results . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

Appendix ~ Data for Longitudinal Stability Axis and Lateral Body Axis Systems . . . . . . . 7

I

Tables . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

Figures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

~ I References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63

iii

Summary

The investigation discussed herein is part of a

broad NASA research program to obtain fundamen-

tal aerodynamic information regarding advanced tur-

A limited experimental investigation was con-

boprop installation effects (ref. 3). This investiga-

ducted in the Langley 4- by 7-Meter Tunnel to ex-

tion was conducted with a representative advanced

plore the effects of aft-fuselage-mounted advanced

transport model modified to incorporate several ar-

turboprop installations on the low-speed stability

rangements of aft-fuselage-mounted single-rotation

and control characteristics of a representative trans-

or counter-rotation propellers. This test examined an

port aircraft in a landing configuration.

aft-fuselage-mounted single-rotation tractor configu-

In general, the experimental results indicate

ration and an aft-fuselage-mounted counter-rotation

that the longitudinal and lateral-directional stability

pusher configuration with the aircraft model in a

characteristics for the aft-fuselage-mounted single-

part-span-flap landing condition. The report de-

rotation tractor and counter-rotation pusher pro-

scribes test results in terms of aircraft stability and

peller configurations tested during this investiga-

control as well as longitudinal and lateral-directional

tion are acceptable aerodynamically. For the single-

control surface effectiveness. Ground effects and

rotation tractor configuration, the propeller-induced

engine-out characteristics are also presented. The

aerodynamics are significantly influenced by the in-

tests were conducted in the Langley 4- by 7-Meter

teraction of the propeller slipstream with the pylon

Tunnel for Reynolds numbers (based on wing mean

and nacelle. This resulted in a nose-up or destabi-

geometric chord) of 0.51 x lo6 and 0.93 x lo6.

lizing pitching moment. The stability characteris-

tics for the counter-rotation pusher configuration are

Symbols

strongly influenced by propeller normal forces. This

configuration provided stabilizing pitching-moment

The longitudinal forces and moments presented

characteristics and, above stall, a substantial increase

in this report are referenced to the stability axis sys-

i n lift.

tem, and the lateral-directional forces and moments

The longitudinal and directional control effective-

are referenced to the body axis system. The moment

ness. engine-oiit characteristics, and ground effects

data are referred to a moment center on the model

are also presented. In addition, a tabulated presenta-

centerline located at the longitudinal location of the

tion of all aerodynamic data presented in this report

wing quarter-chord point. This quarter-chord loca-

is included as an appendix.

tion is calculated for the mean geometric chord of

the trapezoidal wing planform (without trailing-edge

Introduction

extension) that extends from the model centerline

to the wing tip. The aerodynamic coefficient data

Severai studies have ldentlheti potentiaiiy signif-

are based on the trapezoidal wing planforin, which

icant fuel savings for advanced turboprop-powered

has a reference area of 11.21 ft2, a reference span

transport aircraft (for example, refs. 1 and 2). The

of 10.59 ft, and a reference mean geometric chord of

results of these studies indicate that both wing-

13.44 in.

mounted and aft-fuselage-mounted advanced turbo-

All iiieasurenients and calculations were made in

prop configurations appear feasible and that config-

U.S. Customary Units. The capitalized expression

uration selection will depend on further information

in parentheses next to the symbol is the computer

regarding acoustic treatment requirements, struc-

printout equivalent of that symbol that is used in

tural weight, and engine/airframe installation aero-

the tabulation of the aerodynamic data presented in

dynamics. Although decades of experience exist with

the appendix.

propeller-driven aircraft , this experience has been for

configurations having significantly lower power load-

b wing span, ft

ings than those presently considered. A major uncer-

C D (CD) drag coefficient, Drag/qS

tainty associated with the aerodynamic characteris-

tics of advanced turboprop aircraft configurations is

lift coefficient, Lift/qS

CL

the lack of information regarding the effect of the

c ; ; (CRM) rolling-moment co-

highly loaded turboprop installation on aircraft sta-

efficient , Rolling

bility and control during the takeoff, climb, and land-

moment /qSb

ing phases of flight. These technical uncertainties are

most pronounced for aft-fuselage-mounted turboprop

effective dihedral paranie

configurations. This report addresses these technical

ter based on increment of

uncertainties pertaining to the landing phase of the

Cl between /3 = -5' and

flight envelope.

5 O , aCl/ap, per degree

lift-drag ratio

free-stream Mach riurriber

propeller rotational

speed, rps

free-stream dynamic

(Q)

pressure, lb/ft2

wing refcrerice area, ft2

propcIIcir disk area, ft2

propeller tlirust coef-

ficitwt (triode1 refer-

c w x ’ systciri) , Propeller

t tiriist/qS

propeller thrust coeffi-

cient (propeller refer-

cwcc’ system) , Propeller

t h r i i s t / y S ~ ~

i i i a x i i i i i i i i i airfoil

t hickiiess-chord ratio

free-stream velocity,

ft/sec

latcwil dinlension, ft

Y

(Y ( A L P H A ) xiigle o f attack of modcll

rc.f(wticc centerline,

positive nose up, dcg

(BETA) ttiiglc of sideslip of niodcl

P

reference centerline,

positive nose left, deg

A iiicreirietitrtl v:tluc>

rudder deflection atiglc.

4-

positive for trailing cdgch

Irft, dcg

iioiiditiicnsional wing

sciiiispati locat ion

frcc-streail deiisity,

slugs/ f t :{

w wing turboprop concepts, as discussed in the appendix of

reference 9.

Abbreviations (fig. 7):

CR counter rotation

Tests and Corrections

SR single rotation

The tests were conducted in the Langley 4- by

7-Meter Tunnel, which has a test section 14.50 ft high

Model

by 21.75 ft wide by 50.0 ft long (ref. 10). The wind-

tunnel tests were conducted at free-stream dynamic

Sketches of the model indicating the single-

pressures of 6.0 and 20.0 lb/ft2 with corresponding

rotation tractor and counter-rotation pusher pro-

Reynolds numbers of 0.51 x IO6 and 0.93 x lo6, based

peller configurations examined in this wind-tunnel

on the reference mean geometric chord of 13.44 in.,

test are shown in figure 1, and pertinent model geo-

and corresponding Mach numbers ( M ) of 0.06 and

metric characteristics are summarized in table I. This

0.12. The model was tested through an angle-of-

niodel was obtained by modifying an existing Lang-

attack range from -5" to 20" and an angle-of-sideslip

ley model from the NASA Energy Efficient Transport

range from -5' to 10". Tests were conducted with

(EET) program. (See ref. 4 for a description of the

the model positioned near the tunnel centerline to

original unmodified model.) The modifications con-

simulate free-stream conditions. Ground effect con-

sisted of increasing the fuselage length, removing the

ditions were simulated by lowering the model toward

wing-mounted turbofan nacelles, and adding hard-

the tunnel floor. According to reference 11, this

ware options for various aft-fuselage-mounted pylons

method of ground effect simulation is appropriate for

and nacelles. A detailed sketch of the aft end of

the conditions present during this investigation.

this model indicating the geometric characteristics

The aerodynamic forces and moments were mea-

of both propeller configurations is presented in fig-

sured with a six-component strain-gauge balance

ure 2. The model high-lift system, which is the same

mounted inside the fuselage such that the model and

as that described in references 4 and 5, consisted of

balance moment centers were coincident along the

a leading-edge slat deflected 50" and a two-segment

model centerline. The balance characteristics are

trailing-edge flap system, with vane and flap each

summarized in table 11. The angle of attack was set by

deflected 30" as shown in figure 3. Detailed coordi-

the pitch drive of the model support system and was

nates of the wing and flap component surfaces are

measured by an electronic inclinometer mounted in-

given in references 6 and 7. The landing gear ar-

side the forward portion of the fuselage. The sideslip

rangement was the same configuration used in refer-

,.,:.,gle 7:;ss set b ; . t h e ) . a n . &-!..e of the 1nn.1eI c!!nnnrt I I

ences 4 and 5.

system and was measured by an electronic counter

The single-rotation propeller tested was a model

mounted to the yaw-drive gearing system.

of the SR-2 eight-blade design and was 16.9 in. in

Wind-tunnel jet-boundary corrections were deter-

diameter. The counter-rotation propeller also used

mined according to reference 12 and were applied to

the SR-2 eight-blade design, but with two four-blade

Wing, body, and wake

the force and moment data.

propellers (referred to as "four-by-four blade pro-

solid-blockage corrections were also applied to the

pellers") turning in opposite directions, and it was

data and were determined according to reference 13.

16.1 in. in diameter. Photographs of the single-

No corrections were made t o t,he data because of tun-

rotation and counter-rotation propeller systems are

nel flow angularity or support system interference.

presented in figure 4. Photographs of the model

mounted for tests in the Langley 4- by 7-Meter Tun-

Presentation of Results

nel are shown in figure 5. Geometric characteristics

of the SR-2 blades as well as of the pylon and na-

The results and discussion are presented accord-

celles are described in reference 8. Both the single-

ing to the following outline:

rotation and counter-rotation propeller systems were

Figure

powered by a 29-hp (at 10 000 rpm) electric motor

Isolated propeller characteristics . . . . . 6, 7

that provided niaximum power loadings of 14.6 and

Longitudinal aerodynamic

16.1 hp/ft2, respectively. These power loadings are

characteristics . . . . . . . . . . . 8 to 12

substantially lower than those currently considered

Lateral-directional aerodynamic

for full-scale advanced turboprop applications. How-

characteristics . . . . . . . . . . 13 t o 18

ever, because the wind-tunnel velocity is a variable,

Listed on the appropriate figures are the run

properly matching the propeller characteristics in CO-

numbers corresponding t o the data plotted. The

efficient form enables the present tests to simulate

tabulated data for the longitudinal stability axis and

the aerodynamics of higher power loading, advanced

The side force is significantly reduced for the

cotiriter-rotation system (composed of two propellers

turning in opposite directions) compared with the

single-rotation system. The propeller iioririal force

results from flow turning as it passes through the

propeller disk at angle of attack. The substantially

higher normal force produced by the counter-rotating

propellers indicates that the counter-rot ation system

is riiorc’ effectivc in turiiiiig t h e flow.

Aerodynamic Characteristics of Advanced

Turboprop Transport Model

related to the direction of propeller rotation. Dur- were the result of the propeller side force. (See fig. 7.)

ing these tests, the single-rotation propellers rotated As the model was sideslipped, each propeller was at downward inboard. This would result in an effective a sideslip incidence angle that produced a propeller downwash (related to the swirl component of velocity side force which resulted in a model normal force.

in the propeller slipstream) acting on the pylon sur-

Since the direction of propeller rotation on either side

faces; this downwash results in a positive increment

of the model was opposite, the normal force produced

in pitching moment. This gener-

by each propeller was of opposite sign.

ated a net negative aircraft-model rolling moment

j

By contrast, the pitching-moment characteris-

that increased with thrust at low angles of attack

tics for the configuration with the counter-rotation

(fig. 14). There was also a departure from the power-

pusher installation (fig. 8(b)) show a marked increase

, off curve above the stall angle of attack. There was a

in longitudinal stability with increasing thrust and

minimal influence of thrust on the directional stabil-

angle of attack. As angle of attack is increased, the

ity parameter Cna and the side-force parameter Cya

large normal force produced by the counter-rotation

for angles of attack below stall.

propeller system provides a strong stabilizing force

that continues beyond the loss in horizontal tail ef-

For the counter-rotation pusher configuration, in-

fectiveness. The thrust effects noted for both tur-

creasing thrust had a minimal effect on Cia. This was

boprop configurations would not adversely affect the

due to the fact that the side force produced by the

aerodynamic feasibility of these arrangements.

counter-rotation propeller at angle of incidence was

substantially lower than that by the single-rotation

Horizontal tail aerodynamic characteristics. The

propeller. However, an increase in Cn, resulted from

effect of horizontal tail deflection on the longitudi-

adding thrust to the counter-rotation pusher config-

nal aerodynamic characteristics is presented in fig-

uration. As was the case with longitudinal stability,

ure 10. The effect of thrust on horizontal tail con-

trol effectiveness is presented in figure 11. As shown,

peller normal force produced by the counter-rotation

the horizontal tail effectiveness was not significantly

system at angle of attack. In the directional sense,

influenced by increasing thrust for either propeller

sideslip would represent an incidence angle in the

configuration.

lateral plane and, thus, the propeller would pro-

duce both a negative side force (corresponding to

Effect of thrust in ground effect. Ground effect

the previously discussed propeller normal force) and

tests were conducted and the results are presented

a restoring moment. The slight negative increment

in figure 12 for the model at an angle of attack

Cy,> is probably a component of this propeller riorrrial

of 8". For t h e pol,-;cr-off condition, t h e data E ~ O W

a reduction in drag and an increase in nose-do~vii force.

pitching ~iioiiient as the height above the ground h / b

is reduced. Similar trends were obtained previously

Rudder aerodynamic characteristics. The effect

for t'he turbofan-configured model, and the results

of rudder deflection on the lateral-directional aerody-

are discussed in reference 5. With power on, both

namic characteristics is presented in figure 15. The

propeller configurations had trends similar to the

effect of thrust on C , plotted against 6 , (a measure

power-off condition.

of rudder effectiveness) is shown in figure 16. For

the single-rotation tractor configuration, the rudder

Effect of thrust on lateral-directional aerodynamic

effectiveness is increased with the addition of thrust.

characteristics. T h e effect of sideslip on the lateral-

The slipstream generated by the tractor propeller in-

directional aerodynamic stability characteristics for

creased the dynamic pressure on the rudder, and the

the power-off case and for both propeller configura-

slipstream deflection caused by the rudder increased

tions is presented in figure 13. The static lateral-

its effectiveness. An opposite effect was noted for the

directional stability derivatives derived from these

counter-rotation pusher configuration. As shown in

data are presented in figure 14 for each propeller con-

figure 16(b), for this configuration the rudder effec-

figuration compared with the power-off case. The

tiveness was reduced with increasing thrust. It is pos-

power-off lateral-directional stability characteristics

sible that the sidewash generated by rudder deflec-

obtained were very similar to those of the unmodi-

tion produced an effective flow angularity a t the pro-

fied turbofan model. (See ref. 5.)

peller plane. This effective propeller yaw angle would

For the single-rotation tractor configuration, in-

produce propeller forces causing an aircraft yawing

crements in the effective dihedral parameter Cla be-

moment opposing that produced by rudder deflec-

tween the power-off and two power-on conditions tion. In coniparison with the tractor configuration,

1. The ovcriill longitiidinal and lateral-directional

tlic rudder lias no opportunity t o deflect the propeller

stability charact,eristics of the configuration were

slipstream of the pusher configiiration.

not adversely affected by either the aft-fiiselagc-

mounted single-rotation tractor propeller or

The effect of riglit

Engine-out characteristics.

counter-rotation pusher propeller as compared

engiiie out (propeller allowed to windmill) on the

with the haselirie iinpowercd configiiritt ion.

lateral-directional aerodynamic characteristics is pre-

2 . The interaction of the propellcr slipstrcarn with

sented i n figure 17 for both propeller configurations.

the pylon and nacelle had R significaiit effect 011

I i i rach case it rudder deflection of 30’ was applied t,o

longitutlitiitl stability for t,hc single-rot.iition trac-

provide a restoring inonient to tlie asyninietric con-

t o r configiirxt ioii (with propcllcrs rotating ~ O M ’ I I -

t i i t ioii g(’il(’riitc(l by the right propeller witidrnilling.

niird in1)oiird). This rcsiiltrcl in a nose-iip or

111 ;ill c i ~ ~ . cxctpt for the couiiter-rotatioil puslicr

clcsta1)iliziiig pitcliiiig tiioiiiciit .

cwtiligiiratioii of J = 0.92 (fig. 17(d)), this rudder

:{. Tlic propollcr i i o r i ~ i ; ~ I forces Iiitd it signific;iiit

(I(dl(1ct ioii wits siificictit to ovcrconie the asymnictric

t>ffcct o i i loiigit t i ( l i i i i i 1 stirl)ility for t I I V coutitcr-

ciigiii(>-oiit yii\\iiig iiioiiic1it.

rot i i t i o i i p i i s I i ( ~ c,oiifignriit ion. This coiifigurat,ioii

1);tta for t hc eiigiiic-out yawing rnoniciit, of t,he

proviclc,cl st ahilizitig I,it,chitig-tiioiticiit chitr;jct cr-

si tiglc-rot,ilt,ioii t,r:tctor coiifigliritt,ioli are prcwntctl i n

ist,ics, ant1 ~ l ) o v ( > st,itIl it, provided a. s1ibstatit.iitl

figiirc 18. :Ilso prcsrnt c d is tlic t hcwreticitl variat ioii

incre.;tsc, i i i lift.

o f (’,, with 7 ; . I)ascd oii tlie siiiiplc>relatioiiship

4. The cffccts o f thrust on horizontal tail effective-

ness were niiniiiiiil for both propcllrr configitra-

tions.

5. h t h propeller coiifigurat ions had grouiid vf-

feet, t rerids similar t o thosc of t,lir. iitipowcwd

eo I i d i 1, i o i I .

(i. Tlie singlc-rotation t r x t o r propeller iii(.r(.ilsc(l t I I C

riiddcr cffectivcticss by iricrc.;tsing tlic dyiiaiiiic

pressurc on the rudder. The cotitit c’r-rot,iit,ioti

pitslier propeller dcwcasccl t,hc rudder effect,ivc-

iiws 1)y producing it yawing niottient opposing

t I i x t p r o d ~ i c e d t)y r i t d d c r dcfl(.ct ion.

7. The engitic.-out, iiSyiiitiiet,ric yiLwiiig-nioriiciit,char-

xt,eristics werc approxii1i;itcXly e q i d to niomcwtjs

Summary of Results

produccd by latcral thrust x i i d drag otfsct .

I Appendix

C L , C D , C,,, and L I D (CL, CD, CPM, and L/D,

respectively, in tabular form) are referenced t o the

Data for Longitudinal Stability Axis and

stability axis system; the lateral data Cl, C,, and

: Lateral Body Axis Systems

C y (CRM, CYM, and CSF, respectively, in tabular

form) are referenced to the body axis system. These

The aerodynamic force and moment data, shown

data were obtained during test 284 conducted in the

graphically in figures 8 to 18, are presented in tab-

4- by 7-Meter

ular form in this appendix. The longitudinal data

R U N N l J F S E R 1 9 1 L O N G I T U O I N A L S T A R I L I T Y & X I S AND L A T E R A L EOOY A X I S D A T A 1 E S T N U M B E R ? 3 4 M A C H O I P S F B E T A P D E G A L P H A r O E G 1 C L c o CPM CRM C Y 3 L I O h18 C S F - 0 6 3 5 . 9 9 .01 . 0 3 9 4 - 4 . 9 1 . 9 2 - . 2 1 7 7 - . 4 2 9 7 . 5 1 .590 , 8 7 1 4 - a 0 0 6 5 - . 0 0 7 0 - 0 6 3 5 . 9 9 .01 - 2 . 9 3 . 9 2 . Z O n 6 -.3905 - 5 7 0 9 - . 0 0 5 3 - . D O 6 9 -.53 , 5 9 4 . 0 2 9 1 - 0 6 3 5 . 9 9 .01 -1.11 . 9 2 - 5 9 0 0 - . 3 7 6 6 -1.57 . 5 9 7 .0210 . 0 0 5 2 - . 0 0 5 1 ~ 3 1 0 5 .Ob3 5 . 9 9 .01 .oo . 9 2 - 8 1 7 9 -2.20 . 5 9 9 .0144 - . 3 7 2 0 , 0 0 9 0 - . 0 0 2 9 . 1 7 4 5 1.04 5 . 9 9 .01 - 0 2 4 4 - 9 2 1.0186 - . 3 5 0 6 . 0 0 6 5 - . 0 0 6 0 . 0 7 1 8 -2.84 .501 2 . 0 7 . 9 2 l . l P 4 1 - . 3 6 4 1 - . 0 3 8 3 5 . 9 9 . 0 1 - 3 . 2 5 . 6 0 3 . 0 1 9 7 . 0 0 5 1 - e 0 0 5 2 3.03 . 9 2 1 . 3 1 0 6 - . 3 4 4 5 5 . 9 9 .01 - 3 . 8 3 . 5 0 5 . 0 1 3 4 - 0 0 7 8 - . 0 0 2 7 - . 1 3 0 0 -4.12 . 5 0 7 e 0 2 0 0 3.95 - 9 2 1 , 4 1 5 9 - . 3 4 3 7 . 0 0 7 1 - . 0 0 5 1 5 . 9 9 .01 -.1955 , 0 2 3 4 6.13 .92 1 . 7 0 4 3 - . 3 5 1 1 . O O R O -.CO54 5 . 9 9 .01 - . 4 1 0 3 - 4 . 8 5 . 5 1 1 8 . 0 9 . 9 2 1 . 9 3 5 6 - . 3 3 7 5 . 0 0 5 4 -.0073 5 . 9 9 .01 - . 5 9 0 P -5.74 .615 - 0 2 7 6 1 0 . 0 5 . 9 2 2.1600 - . 3 1 5 2 5 . 9 9 .@1 -6.85 . 6 l 9 . 0 2 4 2 -.OO65 - . 7 4 r 7 - 0 0 7 5 1 7 . 1 3 .92 2.3930 - . 0 0 8 1 5 . 9 9 .01 -.9020 . 0 0 5 8 -.2898 - 0 . 2 6 .b23 - 0 3 0 7 1 4 , 1 @ - 9 1 2 . b 0 5 4 5 . P 8 .01 - . 2 6 3 0 -9.91 . 6 2 7 . 0 2 4 5 - . 0 0 8 7 -1.0289 . 0 0 4 0 5 . 9 9 .01 - 1 1 . 5 7 . 5 3 2 - 0 1 7 2 1 6 . 1 3 . 9 2 2 . 6 2 7 9 - . 0 0 0 7 - . 0 0 5 7 - . 2 2 7 2 - 1 - 1 3 6 3 . O l b 9 1P.10 . 9 1 2 . 7 1 6 9 - . 0 1 3 2 5 . 0 0 .01 -.OOb6 - 1 . 3 3 4 7 - . 1 5 9 4 - 1 7 . 0 5 . b 3 6 1 9 . 9 7 . 9 1 2 . 7 6 1 4 5 . 8 a .01 -.0103 -1.4454 - . 0 7 2 0 - 3 7 . 9 5 . 6 4 0 . o o e o -.0133 RUN N U M B F R 192 L O N C I T U O I N A L S T A B I L I T Y A X I S AND L A T E R A L B D O Y A X I S D A T A T E S T N U M B E R 2 0 4 C S F M A C H P I P S F B E T b r D E G A L P H A j D E G J C L C D CPM C R M C Y # L I D 118 .090 1 2 . 0 9 .01 -4.95 1.30 , 0 2 4 4 - . 1 4 1 R - . 0 3 q 1 - 8 7 1 4 . 0 0 0 2 -.0051 3 . 7 2 .is9 .090 1 2 . 0 9 .Ol - 0 1 8 9 -2.93 1 . 3 0 - 2 0 2 0 -.0174 . 6 1 5 9 . 0 0 1 4 - . 0 0 4 2 -11.59 .592 e 0 1 0 4 .090 1 2 . 0 9 . @ 1 -btl.84 . 5 9 b -1.07 1.30 . 5 @ 8 1 - . 0 0 5 5 , 3 7 8 6 . 0 0 2 8 - . 0 0 2 4 - 0 7 1.30 - 6 4 0 1 . 0 0 1 7 . 2 5 5 4 , 0 0 4 2 -.0029 .090 1 2 . 0 9 . 0 1 .Ol2R 5 0 8 . 1 7 . 5 9 ~ . 0 1 4 7 1 . 0 7 1 . 3 0 1 . 0 1 1 7 . O O Y l , 1 5 1 9 .0043 - . 0 0 3 5 -090 11.98 . 0 1 1 2 4 . 7 3 . 6 0 0 .090 1 2 . 0 9 .01 a 0 1 7 2 7 4 . 4 5 , 6 0 2 2 . 0 7 1 . 3 0 1 . 1 7 7 3 - 0 1 5 8 - 0 5 5 4 . 0 0 1 7 - . 0 0 4 7 , 0 1 4 4 5 4 . 2 7 . 6 0 4 2.99 1 . 3 1 1 . 2 9 0 7 .090 1 2 . 0 9 e 0 1 - 0 2 3 9 -.0230 . 0 0 1 9 - . 0 0 4 1 . 0 1 2 4 5 7 . 1 0 . S O 6 4 . 0 3 1 - 3 0 1.4109 .090 1 2 . 0 9 .01 - 0 2 4 7 - . l o 5 4 . P O 3 6 -.OO20 .090 1 1 . 9 0 * 01 . 0 1 5 1 4 2 . 0 6 -510 6.13 1.30 1 . 6 7 1 0 - 0 3 9 7 - . 2 7 9 2 . 0 0 5 0 - . 0 0 3 5 .090 1 2 . 0 9 . 0 1 .0128 3 0 . 1 4 . b 1 4 a . 0 5 1.31 1 . R 8 5 1 , 0 6 2 5 - . 4 4 3 3 . 0 0 3 7 -.0034 . O l b 2 2 3 . 1 0 . b l E 1 0 . 1 2 1 . 3 0 2 . 1 2 3 P .090 1 1 . 9 n .01 . 0 9 1 6 -.6022 . 0 0 3 6 - . 0 0 4 1 - 0 1 0 3 1 9 . 5 4 .622 1 2 . 0 2 1.30 2 . 3 4 0 3 - 1 1 9 8 -.7418 . 0 0 3 2 - . 0 0 4 5 -069 1 1 . 8 7 . @ 1 1 4 . 2 2 1.30 2 . 5 4 5 9 . 1 5 2 8 - . E 7 6 6 . 0 0 2 8 - . 0 0 3 9 .009 1 1 . 9 7 .Ol - 0 1 4 5 1 b . b b . 5 2 7 1 6 . 1 0 1 . 3 0 2 . 5 9 6 1 - 0 0 9 l l . R 7 .Ol - 0 2 0 3 1 3 . 7 9 . b 3 1 - 1 8 R 3 - . % e 3 - . 0 0 5 9 - . 0 0 8 6 . 0 1 8 8 10.31 - 6 3 5 1 7 . 9 8 1 . 2 9 2 . 6 3 2 8 . 2 5 5 4 - 1 . 0 7 5 8 - . 0 0 6 4 - . 0 1 1 5 . O R 9 1 1 . 7 5 .01 2 0 . 0 0 1 . 2 9 2 . 6 7 0 9 - 3 2 7 6 - 1 . 2 1 5 0 - . 0 0 3 4 -.0101 ,089 1 1 . 7 5 .01 - 0 1 0 4 8 . 1 7 .640 P U N H U M R E R 1 9 7 L O N S I T I J D I N A L S T A ‘ I L I T Y 4 1 1 s AND L A T E R A L B’IDY A X 1 5 D A T b T E S T N U I ’ B E R ? P 4 C S F L I D -119 D I P S F E C T 4 , O F G b L P H A r O E G J CL C D C P M C R M C Y 9 - 2 1 4 0 .48 . 5 8 7 6.10 - 5 . 0 3 - 5 . 0 6 - 9 3 - . 1 9 0 2 - . 4 0 9 5 - 7 9 2 4 - . 0 1 4 6 - . 0 4 1 6 . l e 7 2 -.75 . 5 9 1 6.10 - 5 . 0 3 - 2 . 5 6 .94 . 2 0 2 9 - . 3 7 7 3 . 4 0 9 7 -.OOb6 - . 0 4 4 3 . i r 9 3 -1.75 . 5 9 L 6 . 1 0 - 5 . 0 3 - 6 2 6 6 - . 3 5 7 3 , 2 8 5 2 . 0 0 h 0 - . 0 4 3 4 -1.00 .93 . 1 9 3 3 -2.41 . 5 9 6 . 1 5 8 4 .0103 - . 0 4 7 7

6.10 - 5 . 0 3 .oo . 9 4 - 0 5 9 2 -.3568

. 1 7 4 0 -3.01 , 5 9 8 6 . 1 0 -5.03 1 . 0 7 .94 1 . 0 3 7 7 - . 3 + 5 3 - 0 7 9 7 . 0 1 7 4 - . 0 4 2 6 - 1 7 5 9 - 3 . 4 8 - 6 0 0 6 . 1 0 - 5 . 0 3 1 . 9 2 .94 1 . 1 7 3 4 -.3372 - . 0 0 7 5 . 0 2 0 2 - . 0 4 2 4 . I 5 7 7 -3.87 - 6 0 2 1 . 2 7 6 0 -.3301 - . 0 4 2 6 - 0 2 1 1 - . 0 4 2 4 6 . 1 0 - 5 . 0 3 2 . 9 6 .93 - 1 4 6 3 - 4 . 0 4 - 6 0 4 6.10 - 5 . 0 3 4.10 . 9 3 1 . 3 5 6 9 - . 3 3 5 5 - . 1 9 2 5 - 0 2 1 9 - . 0 3 8 0 . 1 5 3 3 -4.b7 . b o 0 5.99 - 5 . 0 3 5 . 9 5 . 9 3 1 . 6 1 1 5 - a 1 4 5 0 - . 3 4 5 2 . 0 2 4 5 - . 0 4 3 0 - 1 5 1 0 -5.97 .512 6.10 -5.03 8.09 . 9 4 . 1 . 0 4 2 P - . 3 0 9 7 - . 5 6 6 3 . O 2 0 8 - . 0 4 2 3 . l 6 4 1 - 6 . 7 8 - 6 1 6 5 . 9 9 - 5 . 0 3 9.98 .93 2 . 1 1 4 6 - . 3 1 1 8 - . 7 7 6 5 . 0 3 2 0 - . 0 4 0 2 . I 6 0 4 -0.22 ~ 5 2 0 6 . 1 0 - 5 . 0 3 1 1 . 9 4 . 9 4 2 . 2 4 7 0 - . 2 7 3 5 -.EO45 , 0 3 1 2 -.OS20 e 1 7 1 1 - 1 0 . 0 6 . 4 2 5 5 . 9 9 -5.03 . 9 3 2 . 5 2 4 1 -.2510 -1.0796 . 0 3 2 0 - . 0 4 0 1 1 3 . 9 6 2 . 5 6 9 7 -.1744 - 1 . 1 4 2 2 . 0 2 4 1 - . 0 5 5 7 . 1 4 1 9 - 1 4 . 7 3 - 6 2 9 5 . 9 9 - 5 . 0 3 1 5 . 9 5 . 9 3 e 1 5 8 6 - 1 9 . 2 3 . 6 3 3 5 . 9 9 - 5 . 0 3 1 7 . 9 9 .94 2 . 6 1 4 4 - e 1 3 5 9 - 1 . 2 0 8 3 . 0 2 9 7 - . 0 4 2 2 . 1 3 7 5 - 4 b . 0 4 . 6 3 n 5 . 9 9 - 5 . 0 3 2 . 7 3 7 3 -.0595 - 1 . 4 6 8 3 . 0 3 9 7 - . C 3 1 4 1 9 . 9 7 .93 T E S T NUPlBER 2 8 4 R U N N U M R E R 1 9 0 L n N G I T U O I N A L S T A B I L I T Y A X I S A N 0 L A T E R A L E O O Y A X I S D A T A C S F A L P H A , D E G J C L C D CPM C R M C Y M L I O d18 M A C H P I P S F B F T A , O E G - 1 8 7 2 8 . 4 1 . 5 8 7 -.@199 . E 5 2 6 -.0092 .090 - 4 . 9 5 1 . 3 7 - . l 6 7 4 -.036P 1 2 . 0 9 -5.03 . 1 5 7 0 - 4 7 2 . 7 0 . 5 9 1 -.0004 . 6 1 @ 7 - . 0 1 1 5 - . 0 3 0 0 . 0 9 1 - 3 . 0 1 1 . 3 3 . 2 0 4 5 1 2 . 2 1 - 5 . 0 3 , 1 2 8 9 1LR.23 - 5 9 4 -1.00 1 . 3 2 . h o b 4 .0047 - 2 6 9 9 .0040 - . 0 2 4 7 -091 1 2 . 2 1 - 5 . 0 3 . 1 5 7 3 2 0 2 . 7 1 - 5 9 6 - . 0 7 .0038 - 2 4 6 8 . 0 1 6 4 - . 0 3 5 9 ,090 1 2 . 0 9 - 5 . 0 3 1 . 3 1 e 7 6 6 4 l b O 4 7 9 . 9 2 - 5 9 8 .0122 , 1 5 1 4 . o l e 9 - . 0 3 5 4 .090 1 . 3 2 . 9 7 2 4 1 2 . 0 9 - 5 . 0 3 1 . 0 4 .~ . 1 4 7 0 1 1 3 . 7 5 . b o 0 . 0 2 9 0 -.0313 .090 .0099 - 0 4 0 2 12.09 - 5 . 0 7 2 - 1 1 1 . 3 2 1 . 1 2 5 8 . 1 5 0 6 5 7 . 7 3 - 6 0 2 - 0 2 9 1 - . 0 3 3 9 . 0 90 1 2 . 0 9 - 5 . 0 3 1 . 3 2 1 . 2 0 8 7 .O2OQ - . 0 1 3 3 2.92 .1393 42.45 .504 . 0 2 9 4 -.0319 .090 1 1 . 9 0 - 5 . 0 3 1 . 3 1 1 . 3 5 5 3 .0319 - . l o 6 9 4 . 1 4 ~ 1 4 1 8 3 2 . 0 3 . 6 O R . 0 2 7 1 - . 0 3 2 3 .090 , 0 4 8 6 - . 2 3 3 7 1 . 3 1 1 . 5 9 6 0 11.98 - 5 . 0 3 6.Oh . 0 7 ? r - . 4 2 2 0 - 1 3 7 1 2 5 . 5 1 - 5 1 2 - 0 3 0 0 - . 0 3 2 3 .090 1 . 3 1 1 . 8 5 5 6 1 1 . 9 8 - 5 . 0 3 8.01 . 1 4 0 2 2 0 . 4 1 . 5 1 6 . 0 3 2 6 - . 0 3 b @ -090 1 . 3 2 Z.O61@ .lo10 - e 5 9 5 9 1 1 . 9 8 -5.03 1 0 . 0 5 , 1 4 2 1 1 9 . 3 1 - 6 2 1 . 0 3 5 4 - . 0 3 6 5 .090 . 1 1 9 0 - a 7 4 5 9 1 1 . 9 8 - 5 . 0 3 1 7 . 2 0 1 . 3 2 2 . 2 9 8 2 - 1 5 1 2 1 5 . 7 9 . 6 2 5 - . 0 4 0 3 - 1 5 6 3 - . E 0 2 8 .O2b0 , 0 90 1 1 . 9 P - 5 . 0 3 1 4 . 0 7 1.31 2 . 4 6 8 7 . 1 5 6 6 1 4 . 2 2 1 0 . 6 4 . 6 2 9 . h 3 3 -.0381 - 0 8 9 1 1 . 8 7 - 5 . 0 3 1.31 2 . 5 7 s 3 - 1 0 1 3 - 1 . 0 4 2 5 - 0 3 0 4 1 6 . 0 2 . 1 5 4 6 - . 0 3 3 6 .089 1 1 . 7 5 -5.03 1 . 3 2 2 . 6 1 9 6 - 2 4 6 1 - 1 . 2 3 5 1 . 0 3 P l 1 7 . 9 9 . 1 1 5 9 0 . 0 0 .63P - e 0 2 4 1 . 3 3 0 b - 1 . 2 7 3 5 . 0 2 9 6 .009 1 1 . 7 5 - 5 . 0 3 2 0 . 0 4 1 . 3 0 ? . t 4 6 3 P U N N U C 9 E P 2 0 0 L P Y G I T D I N A L S T 4 0 I L I T Y X I S 4 N n L A T E R A L f l O Y A X I S O A T 4 T E S T NUWBER 2 0 4 M A C H 0 , P S F R F T A r n F G b L D H A t C E G C R M C Y M L I D hi8 J C l c o C P M CTF -4.91 - 6 7 -.1739 .1130 a7540 .I16 2 0 . 0 0 5.01 - 0 0 4 6 ,0313 -1.10 .507 -,lb32 - 3 . 0 9 - 6 0 .2319 .1110 ~ 5 1 5 4 .I16 20.12 5.01 .Dl46 . 0 2 4 9 2.09 .590 -.1400 - . R 9 . b b .65hP ,116 20.00 5.01 -.DO34 . 0 2 9 4 b.Ob - 5 9 4 .lo84 - 3 1 7 6 -.14b0 .I16 70.11 5.01 . O l - . O O R 3 .0295 7.52 .596 . h b .8h65 .1152 - 2 3 7 3 -.1438 1.01 . 6 7 .9875 .116 70.11 5.01 - 1 2 5 0 e1244 -.00R9 - 0 2 9 1 -.135b 7.90 .598 2.01 .llb 20.11 5.01 . 6 6 1.1060 .1398 - 0 8 3 4 -.0114 .0278 -.I387 7.91 .bo0 2.96 .llb 19.R9 5.01 .Ob 1.2841 .1419 -so433 - . 0 0 9 2 - 0 2 5 9 -.1316 0.05 . b o 2 .117 2 0 . 2 3 5.01 7.92 . 6 R 1.4342 .1524 -a1530 9 . 4 1 .bo4 -.0213 .0251 -.1315 0 . 1 3 20.23 5.01 - 6 1 1.6752 4.90 . 6 0 8 .117 .lb93 -.ZBPl - s o 2 0 8 - 0 2 5 6 -.lZPl 7.98 1.68 1 . R 9 3 0 .117 20.73 5.01 .1928 -e4318 -.0210 .(I233 -.1266 P . d Z - 6 1 2

,117 7 0 . ? 3 5 . 0 1 10.09 1.67 2.0796 ,2239 -.5667 -.0279 .0253 -. 1298 9.29 .b16

.i17 20.73 5.01 1 2 - 0 6 1.67 2.2872 8.96 . h Z O .2553 -.7383 -.0254 .0274 -.129b 70.11 5.01 14.00 1 . 6 8 2 . 4 4 2 9 .116 .29b7 -.E353 -.0276 -0252 -.1202 8.23 .625 16.13 1 - 6 0 2 . 5 0 4 7

.lib 20.12 5.01 .3534 -1.0012 -.0347 .OlZO -. 1077 7.09 - 6 2 9

.116 70.00 5.01 17.95 1.65 2.5396 . 3 8 3 2 -1.OBRH -.0562 - . O D 0 4 -.I165 5.63 .633 .llb 70.00 5.01 2 0 . 1 4 1.66 2.5047 -4641 -1.1701 -.0937 5.53 . b 3 P -.OS92 -.DO67 D U N N I I F R F R 201 L O Y 6 1 T I P I N A L S T I R I L I T Y A X I S AND L 4 T E R 4 L B Q O Y A X 1 5 D A T A T E S r N U V 8 E R 2 8 4 M A C H a . P s f R ~ T ~ , D F G L I D h18 A L D H A r O F G J CL C D C P H C P M C Y H C S F .091 12.21 5.01 -4.95 1.32 -.zo3i - . n z 3 8 .e999 -.1497 8.53 .587 -.on15 .030i .091 17.21 5.01 - 2 . 8 9 1.32 - 2 4 3 5 -.0510 .6315 -.1541 -4.77 .591 . 0 0 4 3 .0355 .091 12.32 5.01 - . q b 1 . 3 2 .6153 -.1436 -14.28 .594 -.0431 - 4 0 5 7 .0709 - 0 3 3 3 .091 12.71 5.01 - 0 4 1.31 .72CO -a0352 .318b ,0025 - 0 3 6 1 -.1560 - 2 0 . 6 0 ,596 1.07 -57.14 .598 .091 12.32 5.01 1 . 3 2 . 9 1 E 9 -.01bl . 2 2 4 0 -.0194 .0253 -.llR3 .091 12.71 5.01 2.03 1.31 1.0810 -.0193 .0973 -.0077 .0329 - . I 4 4 0 -55.92 . b o 0 .091 12.21 5.01 2.96 1.32 1.2146 -.0190 .0471 -61.40 . b o 2 -.Dl42 ,0311 -.1368 4.06 1.32 1.3RZ1 -277.63 .bo4 .091 12.32 5.01 -e0050 -.0911 -.0722 ,0279 -.1282 .091 12.71 5.01 6.02 1 . 3 1 1.5R61 .0111 -.2514 -.0141 .0289 -.I219 142.57 . b o 0 .091 12.21 5.01 R . 0 9 1.32 1.8050 .03r)5 - . 3 6 5 9 -.0204 . 0 2 9 5 -.1282 4 6 . 9 0 .612 .091 12.71 5.01 10.12 1 - 1 1 2.0457 - 0 5 5 8 -.5398 -.OZOO .0350 -.1391 36.63 .blb 27.53 - 6 2 0 .091 12.71 5.01 17.02 1.31 2.2324 .OB11 - . 6 8 3 6 -.0197 .0350 -.1417 .091 12.71 5.01 14.00 1.31 2.4791 .1197 -.E862 -.0296 . 0 2 0 3 -.1199 20.89 .625 .091 12.21 5.01 lh.02 1.31 2.5183 .I611 - . 9 5 Z b - . 0 2 0 5 .0237 -.1207 1 5 - 6 3 10.50 - 6 2 9 - 6 3 4 .090 12.09 5.01 ln.17 1.31 2.5445 . 2 4 2 4 -1.1412 -.0526 .0053 -.1211 -.OPCR 8.lb ,638 .O90 12.09 5.01 2 0 . 0 4 1.32 2.h174 . 3 2 0 9 -1.2573 -.0557 -.DO53 R U N N I I * r ( F Q 705 L O N G I T ' l P l N 4 L S T L R I L I T Y 4 x 1 s A N 0 L A T F R 4 L B O D Y A X I S D A T A T E S T N U r B E R 7 8 4 M A C H 0 , P T F 9 F T b r D F G A L D H A , n F r . J C L c n C P H C U M C V M C S f L 1 0 Y I B -3.93 . O B 0 . n e 3 5.99 .09 8.01 . 9 4 1.7542 - . 4 4 6 2 -.9138 .0055 -.0011 -.0163 .Oh5 h.77 . O 9 R.nl . 9 6 1.b0R5 - . 4 O O b -.7889 -.0013 .0011 -.0322 - 4 . 2 2 - 1 3 1 "01 - 9 5 1.7023 -.3R8O -.I257 -.0010 -.0002 -.0214 -4.39 e199 . O h 4 6.10 .09 - 4 . 2 8 . Z b R . 0 0 3 5.99 . 0 9 H.O1 . Q 4 1.6513 - . 3 P 6 8 -.6320 .0029 . 0 0 2 8 - . 0 2 8 b -4.11 .405 .Ob3 5.99 .09 R . 0 5 - 9 1 1.0174 -.3936 -.5065 - 0 0 7 8 .OD14 -.Dl06 - 4 . 3 6 - 5 4 2 .Oh4 0.10 . O Q n.05 - 9 4 1.0124 -.3698 -.4473 - 0 0 6 5 - . D O 4 3 -.DO09 .0028 -4.13 - 6 2 3 .Ob3 5.99 .09 9.05 .93 1.5905 -.3@56 - . 4 2 9 0 . O O b b - . 0 0 3 9 T E S T N U M B E R 2 8 4 D U N N U R 9 F Q 200 L n N G r T u D I t i 4 L STIRILITY A X I S A N O L A T E R A L Briny A X I S O A ~ A L I O m10 P A C H O I O S F R F T 4 t D E G A L P H b . n E T . J C L c o C P M C D N C Y M C S F -30.60 . 0 0 6 17.09 .09 e.01 1.30 1.0260 -.0597 -.0779 .0003 -.0011 - . O O b 6 .090 -52.53 e131 ,090 12.00 .09 R.O1 1.30 1.0001 - . 0 3 4 3 -.7695 - . 0 0 h O -.OD17 -.0072 . o w 17.09 .09 R.05 1.29 1.7ROR -.0155 -.b731 -.DO22 -.0018 .oooo -115.19 e700 -.5882 - . O n 3 6 - . 0 0 0 5 .DO61 -b59.88 - 2 6 0 .090 12.09 . o o 0.0: 1 . 7 9 1.7717 -.no27 .0006 .DO39 - . O O 5 b 120.30 - 4 0 5 .090 12.09 . 0 9 a.05 1 . 2 9 1.7310 . 0 1 4 4 -.4531 . 0 9 0 17.09 .OP P.05 1.29 1.CRIO .0127 -.4083 a0113 . O n 3 4 -.008@ 132.78 - 5 4 2 17.09 .09 0.05 1.29 1.7153 .02i+ , 4 2 4 7 - . o o + q - . o o v z .0179 80.20 - 5 2 4 .090 T E S T N U M B t Y 2 8 4 L O N G I T U D l N 4 L S l A P I L I T Y @.XIS 4 N O L I E R A L 0 D O Y A X I S D A T A L I D 4 1 8 CPM C R H C Y M C S F A L P H 4 r n F G J c I c 0 .61 -587 . O b 3 5.PP .oo -5.02 .92 -.21hR -.3548 .2294 - . D O 0 8 -.OD52 . 0 2 8 0 ,0093 - . 2 3 .590

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~ 1 0 8 3 1.03 1.02 . 0 0 9 1 - . 0 0 8 1 70.20 .548 .Ob3 5.88 . o o . O D 7 6 .1765 .lo07 2.18 1.00 1.1334 .0059 - . 0 0 4 9 148.87 .600 .Oh3 5 . 8 8 . o o 2 . 9 9 1.01 1.2326 .0530 - 1 3 4 6 . 0 0 2 2 -.0051 23.25 . l o 4 9 .602 .063 5.RR .oo 1.00 1.3946 - 0 3 2 0 . 0 2 6 8 .OB47 4.10 . D O 5 4 -.0020 43.62 - 6 0 4 .Ob2 5 . 7 6 1.00 1.6780 . 0 4 1 2 -.1537 .0901 .oo 5 . 9 8 . 0 0 5 3 . 0 0 0 4 40.76 . 5 0 8 - 0 8 7 2 8 - 0 8 1.01 1 . 8 4 4 0 .Ob27 -.2916 .0095 .GO37 29.39 - 6 1 2 .Ob3 5.88 .on . 0 8 0 9 10.16 1.00 2.0688 .08a5 -.GO96 .00b9 .0015 23.37 . h l b .Ob2 5.76 .oo . O R 3 2 1 2 . 0 5 1 . o o 2 . 7 6 6 4 . 1 4 2 0 -.5667 .0076 . o o + a .Ob2 5 . 7 6 .oo 2.3661 . I 9 4 8 -.6325 - . 0 0 3 2 - . O O Z B .Ob2 5.76 . O P 2 1 1 4 . 0 3 .99 .oo .2131 -.6977 -.0016 .0893 16.05 1.01 2 . 4 0 2 5 -.0055 s o 6 3 5.RP .oo .OB50 18.02 1 - 0 3 2.3957 ~ 3 0 9 4 -.7254 .0083 -.0027 .Ob5 6.22 .oo 2.3537 .3854 -.6981 . 0 0 6 0 .Ob5 6.22 . 0 8 4 4 2 0 . 0 4 1.03 - . @ 0 2 3 .oo L C N F I T U n I N A L S T 4 8 I L I T Y A X I S A N 0 L A T E R A L B r l O Y 4 x 1 s D A T A R U N N U M R E R 345 T E S T N U N B F R 2 8 4 M A C H Q p D S F 9 C T A i " E T . A L I l i A I P F G J CL c o CPR C P M C Y l l L I D H I B C S F -.0920 .090 12.09 . o o - 4 . 0 9 1.40 - 1 2 9 6 -7344 .OOZb -.0282 e1052 -.71 - 5 8 7 .2500 .090 11.90 . o o -2.97 1.40 ,1346 - 5 2 9 0 .0067 -.0285 .IO58 1.86 .591 -I .on . 0 9 0 11.98 .oo 1.39 .6540 e1362 - 3 3 3 9 - 0 1 3 6 -.0277 .lo79 4 . 6 0 .594 , 0 9 0 ll.Q8 .oo .14 1.10 . 8 554 .1400 ,2231 .0138 . l o 8 1 b.11 .596 -.0279 .090 11.67 . 0 0 .99 1 . 4 0 1 .oooa .I 6 8 7 - 1 5 9 6 .DO67 5.93 .59B -,0283 - 1 0 7 2 1.96 1.39 1.1937 .I688 7.07 .bOO .089 11.76 .on . 0 8 2 0 .0056 - . O Z b 9 . I O 4 3 3.0h 1 . 3 2 6 4 .184b .090 11.90 . o o 1.40 . 0 0 2 1 .0107 -.0251 . 0 9 4 2 7.20 .bo2 .090 11.98 . o o 4 . 0 6 1.41 1.4397 -1678 -.Ob62 .0070 -.0257 . l o 2 2 7.67 .604 6.09 1 . 4 0 1.b519 . 2 0 9 0 7.90 .bo8 .090 11.87 . o o -.2OV9 .0072 - . e 2 4 9 - 1 0 7 3 5.12 1.39 1 . R P 4 8 .2175 8.66 .612 . 0 6 9 11.75 . 9 0 -.3455 . 0 0 9 3 -.0227 -0953 2.1163 .090 l l . f l 7 . o o 10.12 1.40 .2508 -.4870 . 0 1 0 9 -.0209 . O R 9 8 8.18 .h16 .090 11.07 s o 0 12.70 1 . 4 0 2.7866 e2757 -.6122 .0077 -.0227 .0929 6 . 3 0 -621 .090 ll.R7 . o o 14.03 1.40 2 . 4 3 4 1 .3190 . O B 8 5 7.63 .b25 -.7265 .00b0 - . 0 2 3 1 1 5 . 9 0 2.4729 .3V56 6 - 2 5 .629 .090 1 7 . 0 9 .oo 1.41 -.78bb - . O O l b -.0277 -091 9 .090 12.09 . o o 1R.25 1.41 2.4679 . 4 4 0 9 -.609b . 0 0 3 0 - . 0 2 5 9 .OPbO >.bo . h 3 4 .090 l l . 9 R .oo 20.08 1.41 2.4732 ,5269 -.7949 .0134 .0917 4.69 .h38 -.0193 R l l N NllM5EQ 374 L O N G l T U n I N I L S T A B I L I T Y A X I S 4 N O L 4 T E R A L R O O Y A X I S O A T A T E S T N U P B F Q 2 R 4 M 4 C H Q r P S F S F T A r O F G A L P M A , O E G J CL C O C P C C P M C Y M C S F L I D t116

-5.05 * * * * .0294 .0023 . 0 0 3 8 . I 4 .585

.092 12.71 - 0 3 .2027 .b127 -.007b -2.9h (1.11 . 0 0 0 4 -.0005 ~ 0 0 1 7 1.95 . 5 6 9 .092 1 2 . 2 1 . 0 3 .3477 -1785 -4171 -1.03 I * . * .0012 . 0 0 0 2 4.27 .592 .091 1 2 . 0 9 - 0 3 .7555 - 1 7 6 8 .2677 . 0 1 2 0 * * * I 4.85 .594 .092 12.21 e 0 3 .09 e 9 2 6 4 .1909 . 2 1 3 3 .0033 -.0001 .004 3 * I * * . 0 9 2 12.71 .03 1.OR 1 . 0 0 8 4 .1985 . 0 8 1 4 - 0 0 4 6 - . 0 0 0 4 .0043 5.08 .59b 12.09 . 0 3 2.19 ***I 1.2781 a1931 -.0269 -.0016 -.0007 .0112 b.36 . 5 9 8 . 0 9 1 **.I . 0 0 1 4 . 0 0 4 2 6.b6 - 6 0 0 .091 1 2 . 0 9 .O1 3.15 1.3672 .2045 -.IO14 - 0 0 4 5

* * * * -.0003 . 0 0 3 4 b.53 -602

. o q i 11.98 .07 4 . 0 8 1.4325 . 2 1 9 2 - . 1 4 6 2 .On50

* * * * 7.09 .bob

.092 17.71 -03 b.11 1.0536 . 2 3 3 2 -.3110 . o o n 9 - 0 0 1 7 -a0004 8.17 * I * * 1 . P 6 4 1 .2534 - . 4 2 2 b . 0 0 3 1 . 0 0 2 2 .0051 7.36 .610 . 0 9 2 12.43 . 0 3 9.99 I * * * - . O O O E .0112 7.24 . 6 1 4 .097 17.37 .03 2.0897 .za85 - . 5 3 0 2 . 0 0 5 1

* * * * 7.49 - 6 1 8

.097 12.32 .n3 11.96 2.7POZ . 3 0 4 4 -.b597 . 0 0 2 4 .0035 -.0072 1 1 1 1 - 0 9 2 17.37 - 9 3 14.04 2 . 4 6 0 9 .353b -.7953 . 0 0 9 3 .0004 . 0 0 9 2 6.96 -623

.***

,002 17.71 . 0 3 15.97 2.4315 .4287 -.e397 - . 0 0 3 + -.0070 .0227 5.b7 .b27

* * * * 2 . 4 4 6 9 -.e977 - . 0 0 9 0 -.0073 .02b5 4.90 . 6 3 2

.097 17.21 - 0 3 1 R . 1 1 . 4 9 9 3 . * I * 4 . 2 8 .537 .092 12.71 . 0 3 70.71 2 . 4 1 9 1 .5657 -.E536 -.0018 -.00b0 . 0 3 Z 9 L n N G I T U O l N O L S L R I L l T Y A X I S AND L A T E R A L B O O ) A X I S O A T A i t s 1 N U M B E R 2a4 A L P H A t l l f G J L I D H I B C L c o C D M C Q M C Y M C S F

- 4 . 9 4 * * * * -.61 - 5 8 7

.lo25 .1687 .b201 - . 0 1 2 4 -.0170 .I454

- 2 . 8 R * * * * .3095 .I751 .4071 -.003b -.GI73 - 1 4 1 3 1.77 .591

1 2 . 0 9 -5.00 -1.03 * * * * ,6135 . 2 2 3 4 . 0 1 1 3 -.@209 . I 4 15 4 . 3 0 .594

. o q i .1590

. a 9 1 17.09 -5.00 .01 * * * * -.0188 .1393 > . 2 8 -596

e 9 0 3 0 . I 7 1 1 - 1 5 1 b .01VI

. 0 9 2 1 2 . 7 1 -5.00 1.05 * * * * e9947 .I737 .05llb .0155 -.0173 .1296 5.73 .598

1 7 . 0 9 -5.00 7.30 * * * * .io14 - . 0 9 3 5 . o l e 3 -.0193 b.67 .bOC

. 0 9 1 . 2 0 9 5 .I321

. 0 9 1 11.98 -5.00 1 . O R * * * * b.66 .bo2

- 3 1 4 6 - 1 9 7 4 -.0264 .0215 -.0175 .1218 7.97 e * * * 1.3952 6 - 6 6 .bo4 . n q i 12.09 - 6 . 0 0 - 7 0 9 9 -.I384 . 0 2 1 4 -.0173 . I 2 4 6 0.03 6.83 - 6 0 8 .090 11.07 - 5 . 0 0 * * * I 1.6676 . 2 4 4 3 -.2581 .0281 -.0127 . 1 1 2 4

.090 ll.fl7 -5.00 7.95 * * * * 1.6457 .0333 -.0128 .1195 7.12 .617

.2592 -.3796

9.95 * * * * 7.10 .b16

.090 11.76 -5.00 2 . 0 6 7 2 . 2 9 1 4 -.5033 . 0 3 0 8 - . 0 1 4 2 .1142

11.9h * * * * 7.02 . h Z O

.090 11.70 -5.00 2.7124 .3150 -.6312 .0371 -.0136 . I 2 3 2 .090 1 1 . 7 6 - 5 . 0 0 1 4 . 0 P * * * * 2 . 4 4 2 8 . 3 4 4 0 -.7596 .0312 -.0162 . 1 2 6 b 7.10 .b75 .090 11.75 -5.00 15.96 * * * * 2.4825 . G I 8 3 - . 6 9 1 4 . 0 2 5 2 -.0195 . I 4 2 4 5.93 ~ 6 2 9 17.99 I * * * 5.16 - 6 3 1 .097 17.71 -5.00 2 . 4 4 4 5 . 4 7 4 2 -.I3796 .0305 -.0179 - 1 3 6 9 4 . 5 2 e 6 3 8

.092 17.71 -5.00 1 9 . 9 0 * * * * 7.4345 . 5 3 8 2 -.E969 .0407 -.0095 . I 3 9 1

P l l N N U M R E P 37h L n N G I T U D I N A L 5 1 4 R I L I T Y A T E S T NUWBEQ 2 8 4 I S A N D L A T E R A L B n o Y A X I S D A T A C d C H O t P T F R F T A t O E G C S F L I O h18 I L P Y A p P E G J C L cn C P U C Q * C Y M

. n q 4 17.77 5.00 -4.94 * * * * -.0717 -.IC36 -.43 .587

1 6 7 9 . b 4 4 2 .0118 . G I 6 1 11.98 5.00 -7.00 *I** . 3 R 8 1 - . 1 2 1 3 2.11 .501 .091 1845 .3935 ,0076 .OlbZ .090 11.87 - . 9 9 I * * * .7674 - . I 1 0 5 4.b9 -594 5.00 lb35 .I871 - . 0 0 5 4 .0157 - 1 0 5.57 -596

.oqo 1 1 . ~ 7 5.00 * * * * .9101 ~ 1647 .1100 -.0128 . 0 1 4 0 -.10R1

.090 11.87 5.00 1.01 I * * * 1.0096 1979 .0403 -.0037 .0192 -.1179

.090 11.R7 5.00 7.OP * * * * 1 . 2 7 1 ~ .i7e2 -.oia2 - . o o o a .0157 -.1116

5.96 -602 .090 11.75 5 . Q O 7.R9 1111 1 . 2 9 8 9 .7178 - . 0 4 2 9 - . 0 0 8 6 . 0 1 b 3 -.IO67

.090 11.75 5 . 0 0 1.00 * * * * -.IO91 b.70 .6OC

1 . 4 1 2 7 .2109 -.I725 -.0120 .OI 76 . O R 9 11.04 5.00 b.11 e * * * -.lo22 7.24 . b o 8 1.6799 . 2 3 2 0 - . 3 7 0 ~ -.015n . 0 1 4 1 P.Oh 8 * * * - . 0 9 3 0 . o q i 1 2 . ~ 9 5.00 1.8527 . 2 4 1 8 - . 4 2 3 3 -.0207 .0138

10.10 b o * * -. 104 b

. n q i 1 1 . 9 ~ 5.no 2 . 0 3 7 2 .)E97 -.5163 -.0197 .Olbb . o o 2 12.32 5.0c 11.97 * * I * -.b511 -.0224 .Ol6l -.O924 2.7339 .3073

.097 I ? . ? ! 2 . 0 0 1 4 . 1 ? * * * * -, 1 0 2 3

2.3578 .3496 -.7503 - . 0 3 1 0 .G108 -.OHbZ .097 17.71 5.01) 1 5 . 9 9 1 1 . 1 .00b4 2.4131 .4Oh2 -.e198 - . 0 3 5 4 - . 0 9 7 8 . o 9 1 17.09 5 . n o I P . 1 1 1 0 . 1 .0079 7.4554 . 4 6 9 1 -.9137 -.0415 11.71 5.00 70.05 * e * * -.0881 . o w 7.377) . 5 6 0 9 - . t l 6 8 b -.0302 . 0 0 3 0 R U N N U M B E R 37 L O N G I T U Q I b J A L S T b B I L I l b X I S AND L b T E R b L B O O Y b X I S D A T A T E S T N U M B E R 2 8 4 M A C H O t P S F B F T A , Q E G A L D H b i Q E G J C L C Q C P M C R M C Y M C S F L I D 4 1 0 -4.97 * * * e .091 12.09 -.02 . 0 4 1 7 - 1 8 5 7 . 5 0 8 8 . 0 0 8 2 -.OOb2 - 0 0 4 5 .22 .587

-e02 -2.99 * * * * - 4 0 3 4 - . O O b 8 -.0037 .0293 2.31 - 5 9 1

. 0 9 1 12.09 - 1 7 4 6 . 3 1 1 8

- . E 8 * * * * 1 7 8 9 7 -.0042 . 0 2 2 1 4.29 .594

.090 11.98 -.02 ,1842 . 1 2 5 4 . 0 0 6 4

-.02 - . O b * * * * . 9 1 6 9 .2144 . 0 4 0 8 . 0 0 0 5 -.0067 - 0 1 7 7 4.28 .596

.090 1 1 . 8 7

1 . O R * * * * l . O f l 8 6 - 2 0 7 2 -.0483 . 0 0 3 7 -.0075 . 0 2 2 7 5.25 .598

.090 1 1 . 9 8 -.O2

7 . 0 8 * * * * 1 . 2 4 1 7 -.0056 - 0 1 1 7

.091 12.09 -.02 - 2 1 9 0 -.1151 . 0 0 4 1 5.67 .boo

3.19 * * * * 1.4086 . 2 1 9 0 -.1790 -.0045 -.OOC7 .0278 6 - 4 1 - 6 0 2

.090 1 1 . 9 8 - . 0 2 . o l e o 6.21 .bo4 -.02 3.09 ***I i.4et.7 ,2395 -.2317 .0091 -.0035 .091 1 2 . 2 1 . 0 2 8 4 6 - 6 4 - 6 0 8

-.02 5.96 * * * * 1.7253 .2523 - . 3 6 4 9 . 0 0 6 0 - . 0 0 6 0

. 0 9 1 12.21

P.10 * * * * 1 . 8 9 9 7 . 0 1 0 5 -.0015 - 2 6 1 5 - . 4 8 2 5 ,0177 7.27 - 6 1 2

. 0 9 1 12.21 -.02 1 0 . 0 6 **I* 2.0704 .3072 -.5bZO .0096 . 0 0 2 1 . 0 0 6 7 6 . 7 4 - 6 1 6 .091 12.09 -.02 .0094 6.65 .bZO -.02 1 1 . 8 1 I*** 2 . 2 2 8 6 .3350 -.6+11 . 0 0 2 7 -.0022 .091 1 2 . 2 1 6.27 ,625

-.02 13.97 * * * * 2 . 3 6 2 9 a3770 -.7308 -.0016 -.0061 . 0 0 0 3

.090 1 1 . 9 8

15.96 **** -.7908 -.0113 -.0131 . 0 2 3 0 5.69 ,629

.09o 1 1 . 9 8 -.02 2.4043 - 4 2 2 3 -.0124 .0106 4.80 .634

-.02 1 0 . 0 3 * * * * 2.4075 .501+ -.e500 -.0073

.090 11.90 -.0056 - 0 0 3 9 4.22 .638

.090 11.75 - e 0 2 20.09 * * * * 2 . 4 0 6 1 - 5 7 0 1 -.E556 - . 0 0 0 6

a B I L I T Y A X I S b N Q A T E R A L O O Y A X I S Q b T A T E S T N U M 8 E R ? 8 4 P U N N U P B E R 380 L O N G I T U O I N A L S C R M C Y M C S F L I D y18 M A C H 0 , o S F 3 E T b r O f G A L P H A r O E G J C L C Q C P M -.05 -4.94 1111 .1900 .2005 - 2 7 3 2 -.0106 -.a025 ,0269 .95 a587 .090 11.98

- 2 . 9 9 * * * * - 4 4 5 0 ~ 1 9 4 8 -.0026 -.0087 .0332 2.28 .590

* 091 12.09 -.05 . 1 4 7 1

-1.03 * * * * .0039 -.0070 .0340 1.17 .i94

.090 11.98 -.05 . 9 7 4 1 - 2 0 9 7 -.0437 4.70 - 5 9 6

.090 -.05 .09 **** . 9 8 1 1 . Z O B b -.0816 .oooo -.0060 . o l e 2

11.98

1.08 * * * * .1202 - 2 1 3 6 - e 1 5 7 3 .a040 - . 0 0 6 0 .O262 5.24 - 5 9 0

.091 12.09 - a 0 5 . 2 4 8 4 - 2 2 6 7 -.1907 .0040 -.0051 - 0 2 3 6 5 . 5 1 - 6 0 0 .090 11.87 -.05 2.12 **I*

* * * * . 4 3 7 9 .2336 -.2618 - .0022 -.0070 .0320 b.16 - 5 0 2

.090 11.87 - . 0 5 3.08 **I* -.0023 .0167 5.89 .bo3 .090 - . 0 5 3.93 . 5 0 0 5 .2548 - . 3 1 8 3 .0114 11.87

* * * * 6 - 4 9 - 6 0 8

6.18 - 7 2 0 9 .2652 -.3935 ,0079 -.0027 ,0181 .089 11.75 -.05 -.4627 .0008 -.0054 . 0 2 b b b.55 - 6 1 2

.090 11.87 - . 0 5 0.14 * * * * . E 0 4 0 , 2 8 8 4

9.99 * * * * 2.0479 .0042 -.0044 - 0 2 7 6 6.26 .bib

.090 11.87 - e 0 5 - 3 2 7 4 -.5254 -.OD30 .0144 b.37 .bZO

.089 - e 0 5 11.96 * * * * 2.2615 a 3 5 5 0 - . 6 1 6 3 . O O Z b

11.76 -.0063 5.08 .625 - . 0 5 1 4 . 2 3 ***I 2.3672 .4029 - . 6 9 8 2 -.0002 .0215 .090 11.87

15.09 * * * * 2.3912 .4290 -.7366 - s o 0 5 7 -.0106 . o l e ? 5.57 .629

,089 11.75 -.05

17.73 * * * * 2 . 3 7 2 1 - 4 9 6 3 - . i i + i -.di054 - . 0 3 8 0 ;0212 4.78 . h 3 3

.090 1 1 . 7 6 -.05 .0012 .0007 3.95 .638 20.05 * * e * 2.3313 . 5 ~ 7 -.7242 .0099 ,089 1 1 - 6 4 -.05 S T b B I L I T Y X I S A N 0 b T E R A L B O D Y A X I S Q A T A T E S T N U M B E R 2 8 4 R U N N U M R E R 383 L O N G I T U Q I N b L C P M C R M C Y M C S F L I D *10 M b C H P t P S F B E T b e Q E G b L P H b t Q E G J C L C Q -.0011 .0172 2.19 .590

-4.97 * * * * .3980 ,1814 -.4771 -.0041

.090 1 1 . 9 8 . 0 3 .1922 - . 5 3 9 5 - . 0 1 4 6 - e 0 0 2 8 -0130 3.70 - 5 9 3

.oqo 1 1 . 9 8 - 0 3 -3.03 * * * * - 7 1 0 4

-.6129 .OO26 - . O O 4 b . O l e 3 5.29 .597

.03 -.qq **** 1 . 0 4 5 8 - 1 9 7 7

e 0 9 1 12.09 - . 0 0 6 3 -.0063 - 0 1 7 3 5.20 .599

-.Ob * * * * 1.1213 ,2157 -.b193

a 0 9 0 11.08 e 0 3 5.95 . b o 1

1 . 0 8 * * * * 1.2942 .2175 - . 6 1 6 4 -.0044 - . 0 0 4 1 e 0 1 5 1

.090 1 1 . 9 8 .03 6.49 - 6 0 3

2.16 * * * * .2209 -.bo77 .0044 - . 0 0 3 6 .0120

.090 1 1 . 8 7 .03 1 . 4 3 3 6 -.5905 - . 0 0 0 2 -.0041 - 0 0 5 5 6 . 6 8 ,605

.090 11.87 - 0 3 3.08 **** 1 . 5 3 8 1 .2303

. 0 0 5 5 -.OOZE .0096 6.39 .bob

3.97 * * * * 1 .bob1 .2515 -.5925

.090 11.87 .Q3 -.0050 . 0 1 2 2 6.69 . 6 1 1 . 2 6 ? 8 -.5402 - . 0 0 1 5

.089 11.75 . 0 3 6.14 * * * * 1.7912

-.5172 . 0 0 7 b . o o o o , 0 0 5 9 6.57 e 6 1 4 7.95 I*** 1.9037 .2897 .093 12.77 .03 6.98 - 6 1 9 .3005 - . 4 5 0 8 . o o z e - . 0 0 3 4 .0120

.093 12.77 e03 10.32 **** 2.0986

. 3 2 4 6 - . k o h l -.0003 -.0040 .0095 6 . 7 5 .623

12.03 * * * * 2.1919

. o w 12.88 . 0 3

. 0 0 2 5 -. 0009 -e0039 6.53 .h27

13.78 * * * * 2.3019 - 3 5 2 0 - . 3 3 0 1

,092 1 2 . 4 3 - 0 3 - . 0 0 8 5 a 0 1 4 4 5.84 e632

1 5 . 9 9 * * * * .3903 -.2399 - . 0 0 3 5

.090 11.98 - 0 3 2.2810 4 . 8 3 eb3b .4697 -.1793 -.0055 -.0114 e0153

10.03 * * * * 2.2665

.090 11.87 . 0 3 - 0 0 1 7 -.0045 . 0 0 7 0 4.19 . b 4 0

1 9 . 9 8 * * * * 2.2292 ,5321 - . l o 1 7

,090 11.98 .03

TABLE I . MODEL GEOMETRIC CHARACTERISTICS

Fuselage: Body station of fuselage nose. in . . . . . . . . . . . . . . . . . . . . . . .

-2.715

Length, ft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.9‘3

hZaximuin dianieter. in . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.8

:Irca (ti.apezoida1 reference). ft . . . . . . . . . . . . . . . . . . . . . . . 11 . 21

Area (wct ted), ft2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.31

Spt11. f t . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.50

Q u r t cr-ctiorcl sweep. (leg . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

/Ispect. ratio . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

Taper ratio (trapezoidal refcx-cricc) . . . . . . . . . . . . . . . . . . . . . . 0.4 12

Reference geometric chord. in . . . . . . . . . . . . . . . . . . . . . . . . .

13.44 Dihedral. ckg . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

Root incidence. deg . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . -1

Body station of wing Icading edge at root. ft

. . . . . . . . . . . . . . . . . . . 5.01

Body station of rrioriieiit reference center. ft . . . . . . . . . . . . . . . . . . . 6.54 Sidc-of-l)ody airfoil ( q = 0.108):

Ctiord . i i i . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22.14

( ! / r ) l , . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.144

. .

Iwist. (leg . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.5

‘I’railiiig-cdgv t)rc . .tk airfoil ( t i = O.434):

(‘tiord. i i i . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.4

(!/c)lll;Lx . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.12

I wist. clcg . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.5

Tip airfoil (‘1 = 1.0):

Ctiorcl> iri . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.41

(!/r)lll:Lx . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.107

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . -0.7

Twist. dcg

Ilorizorit al t a i l : “

r ~ r ( > n . rt. ? . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5

spill . ft. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 . 1 4

Aspect ratio . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . :%.78

Quarter-chord swec‘p. dcg . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

l)ihcdi.al . (leg . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

l’;ipcr rat i o . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.36

MC;LI~ gcotuct ric chorcl. in . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.0

13ocly statioii of tail Icadirig d g e a t root. ft 14 . . . . . . . . . . . . . . . . . . .

I{ oo t a i r foi 1 :

Ctiord> iii . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19.2

(!/r)lll., . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.095

Tip airfoil (sgiiiiiir~tric):

(‘tiorcl% i i i . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.0

( f / ( a ) 1 1 , . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.0x5

TABLE I . Concluded

Vertical tail:

Area. ft2 2.82

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Height. in 19.05

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Leading-edge sweep. deg . . . . . . . . . . . . . . . . . . . . . . . . . . 15.75

Body station of tail leading edge at root. ft . . . . . . . . . . . . . . . . . . . 9.43

Root airfoil:

Chord. in 23.42

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

(t/C)max 0.12

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Tip airfoil:

Chord. in 19.21

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

( t / C ) m w 0.12

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Pylon:a

Area (trapezoidal reference), ft2 . . . . . . . . . . . . . . . . . . . . . . . . 3.8

Span. ft 2.89

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Aspect ratio 2.2

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Quarter-chord sweep. deg . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.0

Dihedral. deg 16.1

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Taper ratio 0.63

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Body station of pylon leading edge at root. ft . . . . . . . . . . . . . . . . . . 9.88

Root airfoil:

Chord, in 19.6

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

(t/c)max 0.12

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Side-of-nacelle airfoil:

Chord. in 12.4

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

(t/C)max . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ii.i'i

Propellers: Single rotation:

16.9 Tip diameter. in

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Maxinium nacelle diameter, in . . . . . . . . . . . . . . . . . . . . . . . . 6.0

at propeller disk, f t . . . . . . . . . . . . . . . . . . . . . . . 9.2

Body station

Counter rotation:

16.1 Tip diameter, in

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Spacing between blade disks, in . . . . . . . . . . . . . . . . . . . . . . . . 2.3

Maximum nacelle diameter, in . . . . . . . . . . . . . . . . . . . . . . . . 6.0

12.4 Body station at forward propeller disk . ft . . . . . . . . . . . . . . . . . . . .

aDihedral not included in span and area dimensions .

TABLE 11. STRAIN-GAUCE BALANCE CHARACTERISTICS

Maxiiriuiri load Ace u rac y

3 000 f 15

f 2 . 5

f125

25 000

9 900 f 4 9 . 5

10 000 f 5 0

f 5

1 000

(a) Plan view and side view

Figure 1. Geometric characteristics of model with aft-fuselage-mounted turboprops installed. All dimensions are given in inches.

C o u n t e r - r o t a t i o n Dusher DroDellers

\ \ It""// I I

\

S i n g l e - r o t a t i o n t r a c t o r p r o p e l l e r s

(1)) Isoniet ric sketch of propeller installatioils.

Figure 1 . <'oricliidcd.

pusher

Single-rotation tractor

Fuselage reference plane

Moment reference center

Figure 2. Sketch of modified aft end indicating geometric characteristics of single-rotation tractor and counter- rotation pusher configurations. All dimensions are given in inches.

Main

Vane

Slat

Figure 3. Cross-sectional view of wing and high-lift system, G a, 4 4 a,

a

El

a

c

.&

Y cd

z

a, u F :

-

e

v i a, a,

a

El

a

E .4 u d u

El

d, M E .e i/) h cd v

I

& a, U h D v

1.2 r-L

e”

d

.e U

s

2 Ln

bo cd d C .e U L d U

E

-

bo d .e

c n

1 c; N

1 4

0 0

N 03 .T 0 n

m

n n a , m rl t . 0

c

*

a

n a , a ,

a

c

m

a

a , !4

a

a ,

a

w

c

4 z

u V

m U

aJ

v I I

a

! 4 !4 a ,

n

I+ a ,

E 3

n

a , &l

a

e

%

!4 a, m

a

a w

e

h I

e

U I

s

!4 b 0 .d

w

cu

UY 3 c 4 0 Q - J N O - G

- w

- a

U U U I I

a

u

M a,

a

d G V w cc) w N

u l

Lo $4 a , d a ,

a

N 0 m

cn

$4 P i 4 3 N

b cn cn

3 3 cc)

0 0

3s

(13 a ,

a

F

'4

L"

d :

r!

"

-

?

r!

0 0 O Q A

t

L"

I d N N rD v- N Ll4

m

t d I I

a

V i

-?

II

h n e v J E V U

a

V t9 a ,

a

V V

n

e i

o !

I I

E U

4 1

c

.e -G N d 4 1 m L .

w X N 5

a

u cc

0 r-l

m

c

B b

a, 8

d r i a, tQ in

a hl

a, 5

0 c n

m

a 0

3 b P 4 4 3

I

I m

I I

I

F 4 I w N m

a

w m X Ln r n

u

b B a, d a,

n 4 4

0 0 . 3 b 4 4

1 4

I m

I

i

I

0 I ?

Ln I I E V U

Run

J T x 2

0 280 P r o p e l l e r s o f f

1 . 4 1 0.09

0 338 1.01 . 3 3

C

m

0 .05 . l 0 .15 .20 .25 .30 .35 .40 .45 .50 .55 .60 .65 .70

h / b

(a) Single-rotation tractor configuration.

Figure 12. Effect of ground height and thrust on longitudinal aerodynamic characteristics. a = 8"; it = 0"

T X 2 J

Run

0 280

P r o p e l l e r s o f f

1 . 3 0 0.21

0 206

. 9 2 . 6 3

0 205

Run

B y deg

0 375 -5

0 374 0

0 376

C

n

-8 - 4 0 4 8 12 16 20 24

a , deg

(a) Power off (propellers off).

Figure 13. Effect of sideslip on lateral-directional aerodynamic characteristics

Run 6 , d e g

0 305 -5

0 299 0

302 5

a , d e g

(b) Siiiglc-rotatioil tractor coritigiirat ion. J = 1.4 1

17igurc 13. Coritinued.

Run

0 304

-5

.06

.04

.02

-.02

-.04

.04

.02

cn 0

-.02

-.04

.2

.1

-. 1

-.2

-8 -4 0 4 8 12 16 20 24

a , deg

ingle-rotation tractor configuration. J = 1.01.

Figure 13. Continued.

iiun

B, dee

-5

0 192

20 1 5

.06

.04

.02

-.02

-.04

.04

.02

c

n o

-.02

-.04

.2

. 1

-. 1

-.2

-8 -4 0 4 8 12 16 20 24

0 1 , d e g

Run

6, d e g

197 -5

191 0

C

l ?

-a -4 o 4 a 12 1 6 20 24

01, deg

( e ) Counter-rotation pusher configuration. J = 0.92

Figure 13. Concluded.

- F r o p e l l e r s o f f

--- 1 . 4 1 0.09

--- 1.01 .33

I

R

so

J Tc x 2

P r o p e l l e r s o f f

--- 1.30 0.21

--- . 9 2 . 6 3

a

n

B

e

(b) Counter-rotation pusher configuration.

Figure 14. Concluded.

5 1

Run 6r, deg

0 3 7 4 0

0 2 7 9 - 10

2 7 8 - 2 0

A 2 7 7 -30

C

n

a , deg

Run 6 , ’ deg

0 2 9 9 0

0 3 3 2 10

0 3 2 9 20

A 3 2 6 30

.06

.04

.02

C

1 0

-.02

-.04

.04

.02

C

n o

-.02

-.04

.2

.1

-. 1

-.2

-8 -4 0 4 8 12 16 20 24

a’ deg

(b) Single-rotation tractor configuration. J = 1.41.

Figure 15. Continued.

0 295 0

0 331 10

0 328 20

A 325 30

Bun 6 , , dee

1 9 2 0

231 - 10

2 34 -20

A 237 - 30

.06

.04

.02

-.02

-.04

.04

.02

C

n 0

-.02

-.04

.2

.1

x

-. 1

-.2

-8 - 4 0 4 8 12 1 6 20 24

a, de&

(d) Counter-rotation pusher configuration. J = 1.30.

Figure 15. Contiriued.

Run 6 , , d e g

0 191 0

0 23G - 10

0 233 -20

A 236 - 30

C

n

-8 -4 0 4 8 12 16 20 24

a , d e g

w

m

w

I N m

m

N a

a J

U E + aJ 0

a N

0 N 0 I

m c n

+I Ll PI 4 i

I

I i

0 3 m N

0 0 0 0

c

a

w

1 (?

m

m (? \

Ll X

0 m

/!

aJ

c) rl

E+

a J

a d

i N 3 0 Ll +I PI i .-I

I 4

I

m N 4

3 m 0 0 0 0 0 I I I I I

c

Run Power

0 374 P r o p e l l e r s o f f

299 S y m m e t r i c

3 4 2 R i g h t e n g i n e o u t

A 345 R i g h t e n g i n e o u t

C

I

C

n

-8 -4 0 4 8 12 16 20 24

c1, d e s

Run Power A r , deg

0 374 P r o p e l l e r s o f f 0

0 296 S ymme t r i c 0

0 34 1 Q h t e n g i n e o u t 0

30 344 R i g h t e n g i n e o u t A

.06

-04

-02

-.02

-.04

-04

.02

C

n

-.02

-.04

.2

.1

-. 1

-.2

-8 -4 0 4 8 12 16 20 24

a, deg

(b) Single-rotation tractor configuration. J = 1.01

Figure 17. Continued.

iiun Power 6 deg

r '

374 P r o p e l l e r s o f f

192 Symmetric

X i g h t e n g i n e o u t 0 245

A 251 f i i g h t e n g i n e o u t

-06

-04

-02

C

I

-.02

-.04

.04

-02

C

n

-.02

-.04

.2

.1

-. 1

-. 2

-a -4 o 4 8 1 2 1 6 20 24

a, d e g

Run Power A r , d e g

0 374 P r o p e l l e r s o f f

191 Symmetric

0 247 Z i g h t e n g i n e o u t 0

A 250 7 x i g h t e n g i n e o u t

3 0

C

n

a , d e g

(d) Counter-rotation pusher configuration. J = 0.92.

Figure 17. Concluded.

.06

J = 1.01

.04

I

C

n

0 .10 .15 . 2 0

T

References 7. Morgan. Harry L.. Jr.: Model Geometry Description and

Pressure Distribution Data From Tests of EET High-Lift

1. Whitlow. J . B.. Jr.: a i d Sievers, G. K.: Fuel Savings

Research Model Equipped W i t h Full-Span Slat and Part-

Potential of the N A S A Advanced Turboprop Program.

Span Flaps. NASA TM-80048, 1979.

NASA TM-83736. [ 19841.

8. Block. P. J. W.: Installation Noise Measurements of

Goldsmith. I. M.: A S t u d y T o Define the Research and

Model S R and CR Propellers. NASA TM-85790. 1984.

Technology Requzrements for Advanced Turbo/Propfan

9. Coe. Paul L.. Jr.; Gentry, Gar1 L.. Jr.: and Dunham, Transport Aircraft. NASA CR-166138. 1981.

Dana Morris: Low-Speed W i n d - T u n n e l Tests of a n Ad-

Mikkrlson. Daniel C.: Mitchell. Glenn A,; ant1 Bober, 3.

vanced Eight-Bladed Propeller. NASA TM-86364, 1985.

Lawrmcc J.: S u m m a r y of Recent N A S A Propeller R e -

10. Applin. Zachary T.: Flow Improvements in the Circuit

searrh. NASA TM-83733. [1984].

of the Langley 4- by Y-Meter Tunnel. NASA TM-85662.

4 . Morgan. Harry L., <Jr.:and Paulson. John W.. ,Jr.: Low-

1983.

Speed Aerodynamic Performance of a High-Aspect-Ratio

11. Turner. Thomas R.: Endless-Belt Technique for Ground

Supercritical- Wing Transport Model Equipped W i t h Full-

Simulation. Conference o n V / S T O L and S T O L Aircraft.

Span Slat and Part-Span Double-Slotted Flaps. NASA

TP-1580. 1979. NASA SP-116. 1966. pp. 435-446.

12. Gillis. Clartmce L.: Polharrius. Edward C.; and Gray,

5. Morgan. Harry L., <Jr.: Loul-Speed Aerodynamic Perfor-

Jowph L.. Jr.: C h r t , s f o r Determining Jet-Boundary

m a r e of a n Aspect-Ratio-10 Supercritzcal- W i n g Trans-

Corrections f o r Complete Models in 7- b y 10-Foot CYn.ced

port Model Equipped W i t h a Full-Span Slat and Part-Span

Rectangular W i n d Tunnels. NACA WR L-123. 1945.

and Full-Span Double-Slotted Flaps. NASA TP-1805,

(Formerly NACA ARR. L5G31.)

1981.

6 . Howard. Jenny M.: and Morgan. Harry L.; Jr.: Pressure 13. Htmiot. .John G.: Blockage Corrections j o r Three- D~strzbutioriD a t a From Tests of Aspect-Ratio-10 EET Dimensional-Flow Closed- Throat Wind Tunnels, W i t h High- Lift Research Model Equipped W i t h Part- a n d Full- Consideration of the Effect of Compressibilzty. NACA

S p a n Flaps. NASA TM-80082. 1979. Rep. 995. 1950. (Suprrsedes NACA RM A7B28.)

I. Report No. 3. Recipient's Catalog No. 2. Government Accession No.

NASA TP-2535

5 . Report Date

April 1986

6. Performing Organization Code

535-03-12-07

'. Author(s)

8. Performing Organization Report No.

Zachary T. Applin and Paul L. Coe, Jr.

L- 16004

10. Work Unit No.

13. Type of Report and Period Covered

'2. Sponsoring Agency Name and Address

Technical Paper

National Aeronautics and Space Administration

Washington, DC 20546-0001

14. Sponsoring Agency Code

,6. Abstract

A limited experimental investigation was conducted in the Langley 4- by 7-Meter Tunnel to explore the effects of aft-fuselage-mounted advanced turboprop installations on the low-speed stability and control characteristics of a representative transport aircraft in a landing configuration. In general, the experimental results indicate that the longitudinal and lateral-directional stability characteristics for the aft-fuselage- mounted single-rotation tractor and counter-rotation pusher propeller configurations tested during this investigation are acceptable aerodynamically. For the single-rotation tractor configuration, the propeller- induced aerodynamics are significantly influenced by the interaction of the propeller slipstream with the pylon and nacelle. The stability characteristics for the counter-rotation pusher configuration are strongly influenced by propeller normal forces. The longitudinal and directional control effectiveness, engine- out characteristics, and ground effects are also presented. In addition, a tabulated presentation of all aerodynamic data presented in this report is included as an appendix.

17. Key Words (Suggested by Authors(s)) 18. Distribution Statement

Advanced turboprops

Unclassified-Unlimited

Counter-rotation propeller

Stability and control

Aerodynamic characteristics

Subject Category 08

20. Security Classif.(of this page) 21. No. of Pages 22. Price

19. Security Classif.(of this report)

66 A04

Unclassified Unclassified

NASA-Langley, 1986 ~

Mtional Aeronautics and

BULK RATE

Space Administration

POSTAGE & FEES PAID

Code NIT-4

NASA

Permit No. G-27

Washington, D.C.

20546-0001

OM#cial Busmew Penalty lor Private Use, 5300

Overview

Document

NASA

Technical

Paper

c .a-

April 1986

Low-Speed Stability and

Control Characteristics of

a Transport Model With

Aft -Fuselage-Mounted

Advanced Turboprops

Zachary T. Applin

NASA

NASA

Tech n i ca I

Paper

Low-Speed Stability and

Control Characteristics of

a Transport Model With

Aft -Fuselage-Moun t ed

Advanced Turboprops

Zachary T. Applin

Langley Research Center

Hampton, Virginia

r u n s n

Contents

Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

I

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

Symbols . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

I

Model . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3

Tests and Corrections 3

Aerodynamic Characteristics of Advanced Turboprop Transport Model . . . . . . . . . . . 4

Effect of thrust on longitudinal aerodynamic performance . . . . . . . . . . . . . . . . 4

Horizontal tail aerodynamic characteristics . . . . . . . . . . . . . . . . . . . . . . 5

Effect of thrust in ground effect . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

Rudder aerodynamic characteristics . . . . . . . . . . . . . . . . . . . . . . . . . 5

Engine-out characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

Summary of Results . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

I

Tables . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

Figures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

iii

Summary

The investigation discussed herein is part of a

broad NASA research program to obtain fundamen-

tal aerodynamic information regarding advanced tur-

A limited experimental investigation was con-

boprop installation effects (ref. 3). This investiga-

ducted in the Langley 4- by 7-Meter Tunnel to ex-

tion was conducted with a representative advanced

plore the effects of aft-fuselage-mounted advanced

transport model modified to incorporate several ar-

turboprop installations on the low-speed stability

rangements of aft-fuselage-mounted single-rotation

and control characteristics of a representative trans-

or counter-rotation propellers. This test examined an

aft-fuselage-mounted single-rotation tractor configu-

In general, the experimental results indicate

ration and an aft-fuselage-mounted counter-rotation

that the longitudinal and lateral-directional stability

pusher configuration with the aircraft model in a

characteristics for the aft-fuselage-mounted single-

part-span-flap landing condition. The report de-

rotation tractor and counter-rotation pusher pro-

scribes test results in terms of aircraft stability and

peller configurations tested during this investiga-

control as well as longitudinal and lateral-directional

tion are acceptable aerodynamically. For the single-

control surface effectiveness. Ground effects and

rotation tractor configuration, the propeller-induced

engine-out characteristics are also presented. The

aerodynamics are significantly influenced by the in-

tests were conducted in the Langley 4- by 7-Meter

teraction of the propeller slipstream with the pylon

Tunnel for Reynolds numbers (based on wing mean

and nacelle. This resulted in a nose-up or destabi-

lizing pitching moment. The stability characteris-