NASA NACA-RM-A52K13-1953 Tests in the Ames 40- by 80-foot wind tunnel of an airplane model with an aspect ratio 4 triangular wing and an all-movable horizontal tail - high-lift dev.pdf

1、- RMA52Kl3 RESEARCH MEMORANDUM TESTSINTHEAMES40- BY80-FOOT WIND TUNNELOFANAIRPLANE -c t trlz: : DEVICES AND LATERAL CONTROLS ByRalljh W. Franks Ames Aeronautical Laboratory Moffett Field, Calif. IC.1CA. F- - .;i 6 m maw contea lnforDdion 3 Of tin eaploE48 Inn, Tlul 18, U.B.C. -toan-riredmonhproHl%Le

2、dInw. NATIONAL ADVISORY COMMITTEE - FOR AERONAUTICS WASHINGTON February 20, 1953 - .-.- at A h m - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. NACA RM A52Kl3 NATIONAL ADVISORY Cm FOR AERONAUTICS TESTS INTBEAMFS bO- BY%-FOOTWIND TUNNELOFANAIRJ?L

3、ANE MODEL WITH AN ASPECT RATIO 4 TRIANGUIAR WING AND AN ALL-MOVABLE HORIZONTAL TAIL - HIGH-LIFT DEVICESAND LATERALCONIROLS By Ralph W. Franks Tests have been made of a triangular-wing-airplane model equfpped with high-lift devices and lateral and directional controls. The model consisted of an aspec

4、t ratio 4 triangular wing in combination with a fuselage of fineness ratio 12.5; a thin, triangular, vertical tail with a constant-chord rudder; and a thin, unswept, all-movable horizontal tail. The wing had an N namely, the inboard flaps, tne outboard flaps, and.the all-movable horizontaltail. The

5、high-lift devices were the outboard flaps and the inboard flaps. Tests were made with the wing-fuselage-vertical-tail configuration in addftion to the tests of the complete model. The Reynolds number, based on the wing mean aerodynamic chord, was approximately 10.9 tillion and the Mach number was ap

6、proximately 0.13. INTRODUCTION . . The low-speed aerodyna included therein were data covering the effect of horizontal-tail aspect ratio and vertical location. The Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2 NACA RM A52Kl.3 results of the testt

7、sof re.ference I indicated that the horizontal tail having the greater aspect ratio.(4.4) located in the extended wing-chord plane gave the best stability and the lowest drag; therefore, this tail configuration was used inthe present investigation. Presented herein are the results of tests of the mo

8、del with high- lift devices, and lateral and directional controls. The high-lift devices - - =I - included slotted inboard flaps and plain outboardflaps. Three lateral controls were tested; namely, the inboard flaps/the outboard flaps, and the all-movable horizontal tail. In addition, a rudder of co

9、nstant chord was tested as a directional control device. The data herein are - .I presented without analysis to expedite publication. - NOTATION The coefficients and symbols used in this report are defined as rollows and as shown in figure 1, wherein all force.and moment coeffi- cients, angles, and

10、control deflections are shown as positive. All - -.-VT I- - control deflections are measured in.a plane perpendicular to the control hinge line. T; SL angle- of attack of the wing-chord plane-with reference to free stream, degrees b bi b0 bt P wing span, feet inboard flap span (total movable), feet-

11、 outboard flap span (total movable), feet horizontal-tail span, feet angle of sideslip of the model centerline with reference to . 1 free stream, degrees . . . - : _ .-. _-. .- C c wing chord, measured parallel-to wing center line, feet .- .- ._1 mean aerodynamic chord of wing, measured_parallelto w

12、ing center rz CD drag coefficient ,1- . - -. - .- - . -I-.- 1.1 - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM A52Kl3 3 Cl cll CY m A Eav it 1-t L 5 P pb Fv 9 S rolling-moment coefficient lift c0ef.ficien-t pitching-moment coefficient yawi

13、ng-moment coefficient side-force coefficient aide force ss average deflection of the inboard flaps, degrees difference in deflection between any pair of control surfaces used as lateral controls, positive when left-hand surface has the more poeitive deflection, degrees average Peflection of the outb

14、oard flaps rudder deflection (positive when trailing edge moves to left), degrees prefix denoting an increment average effective downwash angle, degrees average horizontal-tail incidence relative to the wing-chord plane, degrees distance from moment center of model to pivot line of horizontal tail,

15、feet lift-drag ratio rate of rolling, radfans per second wing-tip helix angle, radians free-stream dynamic pressure, pounds per square foot wing area, square feet iimoT-%M-= Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 Si so Sr St v W X Y Z clP

16、Cn B % NACA RMA52Kl3 inboard flapY.tirea (total mqvable), square feet Y outboard flap area (total movable), square feet rudder area.(total movable), square-feet horizontal-tail area (total movable),square feet free-stream-velocity, feet per second , airplane weight, pounds longitudinal. coordinate p

17、arallel to modeicenterline, lateral coordinate perpendicular to plane .of symmetry, vertical coordinate perpendicular to wing-chord plane, acl - ( aB dC1 c I a(pb/=) ” ac, t ap aCY ( ap Subscripts inboard flaps outboard flaps -. .- .: . _. - :. horizontal tail. . . -. - ,. feet - -.; y7z feet - - .-

18、IT feet The model used.in the present investigation was that described in - -.- -T- reference 1, with the addition of a-rudder and inboard and outboard - :. _ hen. - - - -. .-.-T _- .-.-I- .- The-trimmed lift-and drag characteristics -for the model in level flight, based.on a 30 oundsp: lotiding, ar

19、e shown in- figure 17. The dashed hortion of the lift curve indicates a region of _. longitudina instabilityvith inboard flaps deflected. This destabi- lizing effect, shown in the pitching-moment curves of figure 14, is believed due to the destabilizing variation of downwash with angle of attack thr

20、ough this region, as indicated in figure 15 by the increasing slope of the downwash curve. The effectiveness of the flaps and the horizbntal tail as lateral controls is shown in figures 18 to 21. The increments of rolling- moment coefficient were obtained from figures 5, 6, 9, and 10 and were baaed

21、on a differential lateral-control d .; _ .-L : 1 - _- -. .- A. .*-.* .:, - I _ - _. .-.x2 .-_ - .-_ .-. 1. - -I - - +v _ ._ _ .LL _A - = - 5 - -.- - a d Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM A52KL3 7 the rapid Increase of pb/2V at h

22、igh lift coefficients is due to the decrease of the damping-in-roll parameter at the higher lift coefficients. The iudder defectiveness, based on a loo rudder deflection with inboard flaps deflected, is shown in figure 23 as well as the effect of the use of the horizontal tail as a lateral-control d

23、evice on the rudder effectiveness. The sideslip derivatives, Cna, CQ, and Cy $ , as measured near O“ of sideslip from the data plotted in figures 7 and 12, are presented in figure 24. Values are shown for the.wing-fuselage-vertical-tail configuration and for the complete model with flap deflections

24、of O“ and 40 in both cases. Ames Aeronautical Laboratory National Advisory Committee for Aeronautics Moffett Field, Calif. REFERENCES 1. Graham, David,and Koenig, David G.: Tests in the Ames 40- by 80-Foot Wind Tunnel of an Airplane Configuration With an Aspect Ratio 4 Triangular Wing and an All-Mov

25、able Horizontal Tail - Longitudinal . Characteristics. NACA RM A?lHlOa, 1951. 2. Tani, Itiro, and Sanuki, Matao: The Wall Interference of a Wind Tunnel of Elliptic Cross Section. NACA TM 1075, 1944. 39 DeYoung, John: Theoretical Symmetric Span Loading Due to Flap Deflection for Wings of Arbitrary Pl

26、an Form at Subsonic Speeds. RACA TN 2278, 1951. 4. DeYoung, John: Theoretical Antisymmetric Span Loading for Wings of Arbitrary Plan Form at Subsonic Speeds. NACA TN 2140, 19%. ,/5* Jaquet, Byron M., and Brewer, Jack D.: Low-Speed Static-Stability and Rolling Characteristics of Low-Aspect-Ratio Wing

27、s of Triangular and Modified Triangular Plan Forms. NACA RKL8L29, 1949. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-8 NACA RM A52K13 TABLE I.- DIMENSIONAL DATA Wing . Area, square feet . . . . . . . . . . . . :. . , . . . . . . Span, feet . , . .

28、 . . . . . .-. :.-. ; ; . . -. i- . . . R?;z . Mean aerodynsmic chord, feet . . . . . . . . . . . . . . . . 11.78 Chord at fuselage center line, feet . . . : . . . . . . . . . 17.68 Aspect ratio . ; . . K . . . . . . ; . ; . ; -. . . .- .- . . . 4.0 -T- - Taper ratio . .-.-. : :. . .Y-. .-;-;-. , .

29、.-; -;-.-.- . .-.-. -O _ _ Airfoil section parallel to model. center line . . . . . . . . . . . ; . . . -. NACA 0003 (modified) _- .-.-. 7.L -y ._ .- _ Slotted, inboard flaps .- -. _ _ _ _. - SJS . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.120 hi/b . . . . . . . . . . . . . . :. 0.539

30、Flap chord, percent wing chord at fuselage center Une . . . 11.1 Outboard flaps so/s . . . . . . . -. . . . . . . . . . I . . . . ,. . . . . i 0.059 ho/b . -. 0.334 _ _. - r: - Outboard flap chord; perkkt wing chord at fuseJ.age. center line . . . . .-. i . . . . . -. . -. . . -. ;-. :.-:. -10.5 Fus

31、elage Length, feet . q . , . . . -. :. . . . . . . . . . . . . . . . . Maximum diameter, feet . . . :-. . . . . . . . . . . . . . . . 5E Fineness ratio . . -; ; . . . ;- . . : ; ;- Y -r ;-; ; . ; . -,- . =:-5o Vertical tau . - _ ._ ._ _ _ _. _ -. -_ .-.-. - -. - St/S . . . . . . . i :. . . ;-. . . .

32、 . ;-. ; -. i . y. i . /oh68 s . . .- . . . r -. r . . -0,941 Rudder chord, feet . . . . ; .- . . . . . . .- . 1 . -. . . . 1.76 Aqect ratio of plan form . . . F. . . . . . . . . . . . : . . 1 Taper ratio . . . -. . . . ; . . 6 . .* . ; ; -; -. . .; . . . O Airfoil section parallel to model center l

33、ine . . . ;- . ; -. ; ; -. . . -. ; . Y -MACA 0003 (modified) _.I c “ I - T- - _ -. - r . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM A52Kl3 9 TABLE I.- CONCLUDED r Horizontal taip St/S.* 0.246 bt/b? . . . . . . . . . . . . . . . . . . .

34、. . . . . . 0.523. Chord at fuselage center.line . . . . . . . . . . . . . . . 5-71 2t/E . . . . . . . . . . . . . . . . . . c . . . . . . . . . 1.735 Aspect ratio . . . . . . . . . . . . . . . . . . . . . . . . . 4.4 Taper ratio . . : . . . . . . . . . . . . . . . . . . . . . . 0.46 Airfoil section

35、 parallel to model center line . . . . modified diamond section (4.2-percent- chord maximum thictiess) Percent chord line having zero sweepangle . . . . . .* . . . . . . . . . . . . . . . 50.0 I Pivot line passes through the 27-percent point of the horizontal- tail chord in the plane. of symmetry. .

36、 t Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-f F u c - lg- l-e - 5 - 6 - I A 8 - 9 - I.0 - 11 - 12 - 13 - TABLE II.- SUMMARY OF CONFIGURATIONS !L?BTED W, King; F“, fuaelage; V, vertical tail; H, horlzontd tail I Provided by IHSNot for ResaleNo

37、reproduction or networking permitted without license from IHS-,-,-,. I L 1 I . II I Nqte : A4 force and moment coefficients, angles and control - surf168 II- - Ii 9.22 . I - . - -r- -. - - -. ll - I I- Dimensions skwn in feet unless other w/se specified Figure 2.- Geometric details of fhe model. Pro

38、vided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-, . Figure 3.- The model ae mounted in the Ames 4-b-by 80doot wind tunnel, Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-14 . lJACA RMA2El3 I I 2 4 6 F/u

39、p coord/nclrss S#ion Lbnpo” Lcwer sMl7ce 0 0./3 226 .4!z -619 I.357 2036 2714 33s 4.on 4.750 2654 11.309 is.963 -0.872 - .554 - .4caB z :rp. .35/ .589 747 .860 905 .9/6 z? -328 - 0.872 - /.a30 - f.086 - /./IS - /./3/ - /J/S - /.086 - /.04/ - I.006 - 0.973 -0.938 -0.905 - 0.610 -tX28 23560 1 0 I 0 Ce

40、nter of / 2. arc 0./7 I -0.87 L E radius: 0.17 . . -Hinge pohis rbr new L3 21 .04 0 a3 0 b 12.5 0 18.6 : h 24.7 0 9 .5 40 Q 6.7 40 . ._ .a3 3 .02 8 -.02 I P S-.03 B -.04 -D6 -4 -2 0 2 4 6 8 /o /2 14 16 18 Angfe af sides . . ? - Provided by IHSNot for ResaleNo reproduction or networking permitted wit

41、hout license from IHS-,-,-Y 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 IHS-,-,-_. I , , , , , , , , , 1 , , , , , , , , , , I, I I I I I I I I I I I I I b-i i i j j i i i I I I I I I I I .2 0 -2 -a Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-