NASA NACA-TN-2080-1950 Wind-tunnel investigation at low speed of an unswept untapered semispan wing of aspect ratio 3 13 equipped with various 25-percent-chord plain flaps《装配有多个25%.pdf

1、wII“_ “iIFOR AERONAUTICSTECHNICAL NOTE 2080-TUNNEL INVESTIGATION AT LOW SPEED OF AN -UNTAPERED SEMISPAN WING Ol? ASPECT RATIOUNSWEPT3.13EQUIPPED WITH VARIOUS 25-PERCENT-CHORD PLAIN FLAPSBy Harold S. Johnson and John R. HagermanLangley Aeronautical LaboratoryLangley Air Force Base, Va.Washington. . .

2、 . . . . . ,.- . .s.-. =-,._ ._- -Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TECHLI13RJwYKAFB,M/l.to.Illllllllllllllllllllllllllll00b5E!50NATIONAL ADVISORY COMMITTEkFOR AERONAUTICSTECHNICAL NOTE 2080WIND-TUNNEL INVESTIGATIONAT LOW Sk OF ANUNTAPE

3、REDSEMISPAN WING OF ASPECT RATIOE,QUIPPEDWITH VARIOUS 25-PERCENT-CHORDPLAIN FLAPsuNswEm3.13By Harold S. Johnson and John R. HagermanbSUMMARYForce and moment data were obtained at low speeds to determine theaerodynamic characteristicsof an unswept untapered semispanwing ofNACA 64AO1O section and aspe

4、ct ratio 3.13 equipped with 2-percent-chordunsealed plain flaps having various spans and spanwiselocations. Liftdrag, pitching-momentjand flap hinge-moment data were obtained for thewing with the various flaps deflectedup to 600 flap deflection, or flapspau and spsmwiselocation produced trends in li

5、ft drag pitchingmoment, and flap hinge moment that were siinilarto but of differentmag-nitudes from those for upswept wings of higher aspect ratio. The incre-ment of lift coefficient due to 30 of flap deflection was relativelyunaffectedby the spanwiselocation of the flaps and increasednearlylinearly

6、 with flap span. Because of the increase in the drag coeffi-cients and the associated decrease in the values of the lift-drag r,atiowith increasingflapdeflection, an advantagemay be gained by limitingthe flap deflection to moderate angles (about 300)2 even though the liftcoefficients increase with f

7、urther increases in flap deflection. “121TRODUCTION “The National Advisory Committee for Aeronautics is conductinganextensive investigationof the lift and control effectiveness ofvarious flaps and control surfaces on wings having plan forms suitablefor trsnsonic and supersonicairplanes. The ultimate

8、 objective is toobtain flap.and aileron design criterionssimilarto those availablefor wings of conventionallow-speed plan forms (references1 to 6). . . . . . . - -Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- .-.”=. . -. - _. -2 NACATN 2080As part

9、 of this broad study, the lift and lateral control character-istics of an untapered”low-aspect-ratiosemispanwing hating variousamounts of sweep and egyipped with 25-percent-chordunsealed plainflaps orailerons having various spans and spanwiselocations are beinginvestigatedin the Lxgley 300 MPH 7- by

10、 10-foot tunnel.“This paper presents the results of the investigationof theunswept wing confiration having an aspect ratio of 3.13 and utilizingthe 25-percent-chordcontrol surfaces as lift flaps. Lift, drag,pitchincreasing either the flap spsm or the flap deflection.resulted in an increase in the li

11、ft at any given angle of attack and .-.-.-.-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.- . -.- .06 NACAw 2080also resulted in au increase in the max- lift obtainable, except forthe model with the inboard half-span snd the full-span flaps deflec

12、ted 600for which a slight decrease in C.- was obtained as the flap deflec-tion was increasedfrom 50 to 600. The incrementallift producedbyunit flap deflection generallydecreased as the flap deflection orangle”of attack was increased;however at low *S of attack thewing with the full-span flaps deflec

13、ted50 and 60 exhibited largerincrementsof lift produced by unit flap deflection than was exhibitedat a deflection of 40 (figs. 3, 4, and 7). -As will be discussed later,the hinge-moment data for the outboard 0.2 flaP (Presentedfor8f = 30 in fig. 5) and the hinge-moment and pitching-moment data forbo

14、th the inboard half-span and the full-span flaps (figs. 3 snd 4, respec-tively) indicate that a region of high loading was located at the trailingedge of the wing near the tip at large effective angles of attack. Thisregion of high loading was apparently accentuatedby large deflectionsof the full-sp

15、an.flap,thereby producing the aforementioned increase ineffectivenessof the flap at large deflections. Asimilar loading dis-tributionwas noted for the unflapped rectangularwings of reference 9at high angles of attack.The values of ACL (fig. 7) obtained with the inboard half-spanand the full-span fla

16、ps deflected 30 aud 600 are sunm.arizedin thefollowing table:Flap spsn af AC!Lbf AACARMA4, 1948._ . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.11TABLE I.DIMENSIONAL CHARACTERISTICSOF THE VARIOUS O.25c FLAPS I!ESTEDON THE WING HAVING AI?ASPECT R

17、ATIO OF 3.13Flap spauwise locationFlap span,Configuration bf MlYfi Yfo (Cu ft) b/2QI 0.968 0 0.968 0.7324DI .726 .242 .968 .5493DI .484 .484 .968 . .3662DI .242 .726 .968 .1831DI .484 .242 .726 .3662DI .4840 .484 .36626.- ._._ ._ _ ._._. . . .Provided by IHSNot for ResaleNo reproduction or networkin

18、g permitted without license from IHS-,-,-.- . - .-. . .12c=t0.625L500NACA TN 2080c = 3.875 . 0.032 b+ -r Origin of axes (0.25E)l._ _ -1 I Ib+ .,hinge(0.75C)12 ,I ! Ik25c+!2hingeNACA 64AOI0 airfoil sectionFigure 1.- Drawing of the unswept semispan-wingmodel having an aspectratioof 3.13. (All dimensio

19、ns are in ft.). Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. I?ACA 2080 . 13e.) .-%. . . 4.:.r-a71kL.! $Jd-8g13z.m.t-l.s$%9%-PI- yfo =o.48. - -.- . - . ._ .-. _ _ _ ._ ._._Provided by IHSNot for ResaleNo reproduction or networking permitted with

20、out license from IHS-,-,-.- . - -. - - . .16CmNACA TN 2080Figure 3.- concluded. . . - -Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. NACATN 2080 . 17. .4.3.2c./o-.4 -.2 0 .2 .6 .8 1.0 12 14.4 CL.Figure 4.- Effect of flap deflection on the aerodyn

21、amic characteristicsin pitch of the unswept wing of aspect ratio 3.13 equipped with full-span flaps f =0.968). yf = o; yfo = o.96.i.- .- ._ _ _._-. ._ ._.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-18. . . . . . .NACATN 2080Figure 4.- Concluded.

22、. -. -. -Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.NACATN 2080 19.Abf Y20 m n,.0 0 Plath wingA .242 0.726/6 v .484 .484 -+ “El .726. .242 1/2 -0 .968 0 “F ,) /A / /d8 / / / ,G / /4 . / P/ / / / /0 K xl )“i/ / / /./-4 6 r).J G“-8 w-.4 -.2 0 .2

23、-4 .6 :8cFigure 7.-Effect of flap span on the aerodynamicpitch of the unswept wing of aspect ratio 3.13. (flaps yfo = o.968). b-f= 300.,.4.3 .2q)./ocharacteristicsinequipped with outboard. -.- .- . . _ _ . _ - - - -.- -_ _._.Provided by IHSNot for ResaleNo reproduction or networking permitted withou

24、t license from IHS-,-,-. .20 NACA TN 2080 .0bf Yfi,z b/2-0 0 Plain wing , -.1A .242 C?726v .484 .484 -.2El .726 .2420 .968 0 1 -.3 El G-.41 10“t%-.4 -.2 0 .2 .4 .6 .8- LO 12 14CLFigure 5.- Concluded. . -. . . .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from

25、IHS-,-,-c. NACATN 2080 a,.cc- ./ c=-A .484 .968 q/6/2 r84D“od -4r d yo .2 .4 .6 .8 Lo 2c.4.3.2 c./oFigure 6 Effect of spanwise flap location on the aerodynamiccharacteristicsin pitch of the unswept wing of aspect ratio 3.13( )equipped with half-span flaps bf . r).48k . bf = 300.- . . .Provided by IH

26、SNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-22. . .NACAII!N2080Cmo-./-.2-.3-.4- / -./ 0 “ /2/ / ./, ; / / -,/ / 4 Y(/ =S=0 10 20 30 40+,degFigure 7.- Variation of incremental lift coefficient50 60with flap deflectionfor the unswept wing of aspect ratio 3.13 eq

27、uipd with inoard half-(span bf = O.; yfo = ) (0.k8$ and full-span bf = o.96; yfo = o.96$).flaps. yfi = 0. . _ Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . .240-.04-.08zbn-.12-.16. -.20-.24NACA TN 2080 . -lllF/f yfo = 0.h8 and ffll-span( )bf =

28、0.96$; yfo = 0.96$ flaps. yfi = 0.-.- - _ _-._Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN 2080 25.4.2000 .2 .4 .6 .8 LO/bfFigure 9.- Effects of flap span and spanwise location on the lift coeffi-.cient of the unswept wing of aspect ratio

29、3.13. bf = 30. . _. . . . . . . . . . . . . . _ ,._ _ . .-. . . . _ _Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-r- . -. - . . . .26 NACATN 2080a.040-.046jn -.08-.12-.16-.2GoI I I I 1 yf = Q968 bi2 - ol =0 -J 1(d:g)1. /2/o .-. 2 .4Figure 10.- Eff

30、ects of flap span andmoment coefficient of the unswept.6spanwise location on the pitching-wing of aspect ratio 3.13. .bf = 300.0 -. . . .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACATN 2080 27.04.03.0/o0yf*Experimental. . 0968.Estimated + - (r

31、eference 10) + !.000Theoretical-(unpublished) = O0 Experimental +01“.2 4bf.6 .8 /.0b/2Figure 11.- Effects of flap span and spanwise location on the lift-effactiveness paraTIIeterCL of the unswept wing of aspectratio 3.13.NACA-Lmey-4-24-50-950. -. . . . .+ _ .-.z - . . -_ _ .- ._ _ . . . _ _Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-