NASA NACA-RM-A52L16-1953 Tests in the Ames 40- by 80-foot wind tunnel of two airplane models having aspect ratio 2 trapezoidal wings of taper ratios 0 33 and 0 20《带有展弦比为2 锥形比为0 33和.pdf

1、RESEARCH MEMORANDUM TESTS IN THE AMES 40- BP 809FOOT WIND TUNNEL OF TWO WINGS OF TAPER MTIOS 0.33 AND 0.20 By Ralph W. Franks Ames Aeronautical Laboratory Moffett Field, Calif. I IUN -a .d- COPY 6 H RM A52LU3 NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS . . WASHINGTON Provided by IHSNot for ResaleNo

2、reproduction or networking permitted without license from IHS-,-,-1P ? 1 NACA RM 526 NATIONAL ADVISORY COMMITTEX FOR RESEARCHMEMOtiUM TFSTS INTHEi AMES kO- BY positive when left-hand surface has the more positive deflection, deg (Subscripts denote the control used: f, flaps; t, horizontal tail.) rud

3、der deflectLon, deg prefix denoting an increment average effective downwash angle, deg average of the.;right tid left horizontal-tail incfdences relative to the wing-chord plane, deg . distance from moment center of model to pivot line of horizontal tail, ft lift-dreg ratio wing taper ratio, tip cho

4、rd/root chord free-strew dynamic pressure, lb/sq ft ting area, sq f-i; * flap area (total movable), sq ft rudder area (total movable), sq ft horizontal-tail erea (total movable), Sq ft vertical-tail area (total exposed), sq ft Provided by IHSNot for ResaleNo reproduction or networking permitted with

5、out license from IHS-,-,-EACARMA52Ll6 4 V w X Y Z free-stream velocity, ft/sec alrplane weight,lb -1ongitudLnal coordinate paralleltomodelcenter line, f-t lateral coordinate perpendica to plBne of Symmetry, ft vertical coordinate perpendicular to wing-chord pm, ft DESCRIpTIOEl OF KIDEL Drsxings of t

6、he complete airplane models are shown in figures 2 A ; and 3, and pertinent dimensional data are presented in *ble I. Photo- graphs of the models as mounted in the Ames 40- by 80-foot wind tunnel are shown fn ffgure 4. The airfoil sectfons of both wings, taken parallel to the model center line, were

7、 IWCA 0005 sections m - The dimensions of the fuselage are given in table I, The fuselage was of circular cross section and had a fineness ratio of 12.5. Fuse- . - lage coordinates are given in reference 1. The vertfcal tail had a triangular plan form with modified _ NACA 0005 airfoil sections (stre

8、amwise) and was equipped with a constant- chord rudder. The rudder had 8 plain radius. nose and 8 small unsealed gap= The horizontal tail had 821 unswept plan form and modified Uamond airfoil sections. The 0rigina.l section of 5.6-percent thickness was modffied by rounding the maxfmum-thickness ridg

9、e using a radius of curvature of 4.48 chord; the resulting section had a maximum thickness of 4.2-percent chord. The three vertical locations of the horizontal tail above the extended Wing-chord plane are given in table I. The trailing-edge flaps were of the slotted type and were of constant chord.

10、Details of the flaps and their path of travel are shoq in figure 6. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-HACA RM A52Ll6 - 5 TEsIsmDPRcmmRE The configurations tested are listed in table II. ! however, tests were made bnfy for the mod hence,

11、 the average angle of flow across the tail Is zero. Under this condftion, eav equals a.+ it. In order to obtain points of intersection for tail incidences other than those tested, a linear varFation of dCm/dit was assumed. The lateral-control data are S uiWfzed in figures 25 to 27. The effectiveness

12、 of the flaps in producing rolling moment is shown in figures 25 and 26. The effectiveness of the horizontal tail as a lateral control is shown in figure 27. The results are compared with the values obtained from the theory given in reference 6. Ir. Y The increments of C b Cn, and-CY per degree of r

13、udder deflection, as measured with 8f = 40 , are presented in figure 28. This figure also shows the effect of use of the horizontal tail as a lateral-control device on the rudder effectiveness. Ames Aeronautic 45% 0.189 0.245 1.76 1.0 0 0.174 0.245 1.76 1.0 0 0.277 0.782 1.71-6 4.: 0.46 O-255 0.751

14、l-585 4.04 0.20 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2P IVACA RM A52L16 4 L 9 TABI;E I.- DIMENSIONAL DATA - Concluded I Horizontal tail (continued) Middle position St/S btb h/E d (b/2) Aspect ratio Taper rat10 I High position St/S btb ZJE

15、-z/b/2) Aspect ratio Taper ratio Wing Taper Ratio o-33 I 0.20 0.225 0.671 1.682 0.260 o.;o 0.335 0.67i l F, fuselage3 V, vertical tail; H, horizontal tail. (Subscripts denote horizontal-tail Lodation: L, low; M, middle3 H, high) 7 U+F+V 0.33, 0.x) 0 0 $0 - - 0 -2e26 0 8 ?J+F+v+EIL 0.33 00 2 0 0 -M2S

16、 -10 U+F+V 0.33 0 0 - 0 0 0 ( 9 p 1 0.20 lo lo 1 zn 1 0 1 0 p6 16 Wm-vML 0.33 iox) -10 0 OW u+F+y 0.33 “, 20 - 0 0 I 17 w+F+v+HL 0.20 -6 0 0 V+F+V 0.20 0 0 18 U+F+V+EL 0.33 Lo -10 x1 0 -a 19 U+F+V+HL 0.33 400 -10 lo 10 -2426 . - * l . Provided by IHSNot for ResaleNo reproduction or networking permit

17、ted without license from IHS-,-,-m2AmA52Ll6 .w . !l!ABm III.- cTlmER=oFtiTY ILnmmJDm LocATIm FOR !I!5 VARrOus coIummATIoNs Tail position Low Middle Hi c , z Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3P (II Model with a wing of taper ratio 0.20.

18、 Figure 4.- Concluded. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-18 I. I- hiotikt center tine I 7- I- 4.12 INCA RM 5216 Area of p/on fwm with sections differing 0.1 percent or less fern the NACA 0005 tmodified/ profile. Note : At/ dimensions or

19、e tn feet contour of fuseloge at wing-chord plane Figure 5.- Areu of wing of taper ratio 0.20 having ukfoil secfions deviuting from those used for fhe whg of taper futio 0.33 . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-!TrY -Hinge poinfs for ti

20、p when &ff&ed fo angles shorn. Sfufibn 0 2 4 6 F/L? Sfufion 0 O./N 226 452 .679 1.357 2CJ36 ziT4 3393 eon 4.750 5654 /.309 /6.963 23560 -mP . L.E coordthofes Lawef sunCDce -0.872 .- 0.872 - -554 - /.a30 - .mB - i-086 - -181 - /./is - .0/2 - /./3/ .35/ - /J/S -589 - / -086 .747 - 1.04f .860 - I.006 .

21、905 - 0.973 .9/6 -0.938 .905 - 0,905 .6/O - 0.610 .328 -Q328 . Figure 6.- Defds of the sloffed, ffuii?ng -edge f/ups. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license

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26、-,-,-P 0. I I I I, I I I I I I I.1 I I I I I I I I I I I I I ,IIIIIIIII”II”“, TIP -.h3 -#,w4?4,02 0 .a2 4x2 cAI/ 0 .or .a2 504 0 .04 09 .&? As 20 .w -2 ” ” ” ” ” ” ” / / i Rolling-momt coeff&nt, Ca Yaw&r- moment mfftci8nt, Cn We -f&e mffkknf, Cy Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-