NASA NACA-RM-A51L03-1952 Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail latera.pdf

1、RESEARCH MEMORANDUM TESTS IN THE AMES 40- BY 80-FOOT WIND TUNNEL OF AN AIRPLANE 13 - AND AN ALL-MOVABLE HORIZONTAL TAIL = CQNF“IfION WITH AN ASPECT RATIO 2 TRIANGULAR WING w l$ i f LATERAL CHARACTERISTICS By David Graham and David G. Koenig Ames Aeronautical Laboratory Moffett Field, - Calif. TQ“ “

2、Y FOR AERONAUTICS WASHINGTON February 11, 1952 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-RESEARCH MEMORANDUM TESTS IN THE AMES 40- BY O-FOOT WIND TUNNEL OF AN AIRPLANE CONFIGURATION WIT AN ASPECT RATIO 2 TRIANGULAR WING AND AN ALL-MOVABLE HORIZ

3、ONTAL TAIL - LA.- CHARACTERISTICS By David Graham and David G. Koenig SUMMARY An investigation has been %de to determine the low-speed lateral characteristics of a triangular-wing airplane model. The model ccnsisted of an aspect ratio 2 triangular wing in combination with.a fuselage of fineness rati

4、o 12.5; a thin, triangular, vertical tail with a constant- chord rudder;. and a thin, unswept, all-movable horizontal tail. The wing had an NACA 0005 modified .section,and was equipped with partial- span, slotted, trailing-edge flaps. Tests were made with the wing alone, wing-fuselage, and wipg-fuse

5、lage-vertical-tail configukations fn additiori to the tests of the complete model. The Reynolds nuiber, based on the wing mean. aerodynamic chord, was approximately 14.6 X 10 and the Mach number was 0.13. INTRODUCTION A study of the low-speed characteristics of an airplane configura- tion with 811 a

6、spect ratio 2 triangular wing and an all-movable horizontal tail has been undertaken in the Ames 40- by 80-foot wind tunnel. The results of tests to determine the longitudinal characteristics, reported in reference 1, showed that of the three vertical positions of the horizontal tail used, namely, 0

7、-, 25-, and 50-percent wing semispan above the wing-chord plane, only the lowest provided satisfactory longi- selected for the investigation of the low-speed aerodynamic characteris- tics of the airplane configuration in sideslip. The investigation also 4 tudinal stability. Accordingly,this position

8、 of the .horizontal tail was - - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-included tests of-the wing alone, wing-fuselage, and wing-fuselage- vertical-tail combinations. The results are presented herein without analysis in order to expedite pu

9、blication. - NOTATION The coefficients and synibole used within this report are defined as follows. and in fiwe 1. The- moment ikta arc referred to a moment center located at 42.6 percent of the mean aerodymmlc chord. angle of attack of the wing-chord plane with reference to . - .- - -. free stream,

10、 degrees .“ . . . “ _“ “. x wing span, feet . horizontal-tail span, feet. r“ wing chord, measured garallel. to- wing center line, feet . . “ “. - - - “ “ . .“ . “ . mean aerodynamic chord of- wing, measured. paYallel .to iring nb/2 4 center line i J, . “ t .I - . feet roiling-moment -coefficfent : -

11、 lift coefficient pitching-moment :caefPicient- (pltchiEzmoment yawing-moment c-oefficient -. side=force ccxf_ficient tide,?- “ ., -_ “ . . rudder deflection, measured perpendicular tq hinge line, degree8 “ E-:!: - Provided by IHSNot for ResaleNo reproduction or networking permitted without license

12、from IHS-,-,-“ NACA RM A5lL03 3 it P pb 2v 9 S St V cp X Y / Z 28 horfzontal-tail incidence relative to the wing-chord plane, degrees distance from moment center of model to pivot line of horizontal tall, feet rate of rolling, radians per second wing-tip helix argle, radians free-stream dynamic pres

13、sure, pounds per square foot wing area, square feet horizontal-tail area, square feet free-stream velocity, feet .per second angle of bank, right bank positive, degrees longitudinal coordinate parallel to model center line, feet lateral coordinate pergendicdar to plane of symmetry, feet vertical coo

14、rdinate perpendicular to wing-chord plane, feet A drawing of the complete airplane model is shown in figure 2, and the pertinent dimensional data are.presented in table I. The model was identical in all respects, except for the addition of a rudder, to that described in reference 1 The constant-chor

15、d rudder had a plain radius nose and a small but unsealed gap. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 The teeta conducted are li8ted in. table 11, which. also 8erves as an. index to .figurea 3 through. 14 whe.re .the dat.a are. presented.

16、. (It should ,- be noted that a dashed-line fairingls used in Iifes“Q, 8, 10, and 14- where the data are incomplete.). .The horizontal-tail incidences were chosen to provide data at lpx t.rim lift cpdficients apd.at trim lift coefficients near thme suitable for landing. The asymmetric flap deflectio

17、ns (fig. 13) were used to give an indication of the effective- ness of. the trailing-edge flaps when used as- ailerons:. The moment data are referred to a moment center located at /.wee of .:- aileron deflectbn, as measured with A - p = 0 and with 6f = 5O and 8, = loo.- The values of damping:ln-ralf

18、 coefficient as given in reference.2 were used-for the computation of pb/2V. The increments of Cz, Cn, and Cy per,-demee .of der deflectiqn, as measured with r = loo, are preselited *.ripe 18. As a final summary, the control deflection necesaary to hold eteady sideslip and - the resultant angle of.

19、bank for the model. with the flaps .deflected 40 are shown tn figure 19 for lift .coefficients of 0.4, 0.8, and 1.2. Although data were obtained only for loo total.aileron. deflection and IOo rudder deflec.tion, the curves of. flgure 19 were extended. to 30 total aileron- deflect3on and to rudder ;

20、0940 , 10 cz, cn, cy PS B 0,8,16,20 -2 +x? NOTE: W, wing; F, fuselage; V, vertical tail; H, horizontal tail. T Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from I

21、HS-,-,-t L 1 t cl p3 I Y Y t X Figure I. - Sign convention for force and moment coefficients. AN force and moment coefficients , angles and control- surface deflections are shown as positive. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-10 -1 I- 9

22、-46 Figure 2. - Geometric defuils of the model. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . 1 . . . . . . 1 I 18 ?2 u1 P 16 F 0 14 9J 12 .o 2- ID t.8 .p 8 G6 I 4 .4 2 0 -. 2 -4 0 4 8 I2 I6 24 0 .I 2 .3 .4 .5 D8 .04 0 -D4 -.08 -JZ Angle of

23、 attack, a, deg Drag coefficient, C, Pitchmg-mament coeffkient, C, I“ I“ Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- . . . . . . . . . . - . . . . . . . - . . . . . . . . . . .; . . . . . . . . . . ,i, I Provided by IHSNot for ResaleNo reproduct

24、ion or networking permitted without license from IHS-,-,-. Ang/e of sides/03 21 1.4 1.2 1.0 t. x- .8 a $ .6 C ea 8 .4 .2 0 e? x- .5 -? C v a 82 8 .3 .1 0 6 2. .04 * s .o t, 8 4 -.w 0 1 -08 I .$ -12 e 2 a -J6 -4 -2 0 2 4 6 8 10 12 14 16 18 Angle of s/des/ip, 4 deg (a) 6 , CD , cm vs 4 Figure 8. - Cha

25、racterisiics in sideshp of the wing-fusehge - veriicai. configuration. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-22 .m 0 -.Ol Angle of sideslip, ,8, deg figure 8. - Conduded. -. Y -. . Provided by IHSNot for ResaleNo reproduction or networking

26、permitted without license from IHS-,-,-. I 18 L4 $6 4 .4 .2 . 0 -4 0 4 8 I2 16 20 24 28 , .04 0 -.04 -.08 -.fZ -,l6 -20 -24 -29 Angle of attack, a, deg Pltduhg-mwnent coefficiennt, C, Drag coefflcient, C, 0 .I .2 3 .4 5 .6 .7 E . Provided by IHSNot for ResaleNo reproduction or networking permitted w

27、ithout license from IHS-,-,-. . . . . . . 18 I M Ui c D e .8 x- . e 2 6 $ .4 P 0 -2 -06 7w .a : 0 .02 . -,Of 0 .Of DP .M .a 05 L% -.A? 48 44 0 .04 .# .f2 I Rolling-moment F Yorring- moment Side -force coefficien4 C, cocfficienf, C coefficienf, C,. I. Figwe S.-Cm I c, I c, vs B figure /O.- Characferi

28、sfics n sides of the comp/efe model I; , Oo, Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-26 +.q- . ;3 40 9 85 40 4 6.6 40 Angle of sideslip, , , -87“. . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from I

29、HS-,-,-. c -.a6 Tar -02 0 Rol/ing-momenf uing -moment Side -force coefficient, 5 coefficient, C, coefficient, C, * . . . . . . . . . . . . . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM A5lL03 L (0) I I cm / Figure 12.- Gharacierisiics in sides/ of fhe complete model. 4 I -IOo. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-