NASA NACA-TN-1517-1948 Wind-tunnel investigation of an NACA 0009 airfoil with 0 25-and 0 50-airfoil-chord plain flaps tested independently and in combination《带有单独试验和一起试验的0 25-和0 50.pdf

《NASA NACA-TN-1517-1948 Wind-tunnel investigation of an NACA 0009 airfoil with 0 25-and 0 50-airfoil-chord plain flaps tested independently and in combination《带有单独试验和一起试验的0 25-和0 50.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-TN-1517-1948 Wind-tunnel investigation of an NACA 0009 airfoil with 0 25-and 0 50-airfoil-chord plain flaps tested independently and in combination《带有单独试验和一起试验的0 25-和0 50.pdf（35页珍藏版）》请在麦多课文档分享上搜索。

1、.-,NATIONAL ADVISORY COMMITTEEFOR AERONAUTICSTECHNICAL NOTENo. 1517WIND-TUNNEL INVESTIGATION OF AN NACA 0009 AIRFOIL WITH0.25- AND 0.50 -AIRJ?OIL-CHORD PLAIN FLAPS TESTEDINDEPENDENTLY AND IN C OMBINATIONBy M. Leroy Spearmbut since cb?agend pltchtng mcmmmt were not of prinwmy importance inthis invest

2、igation,their Palms are not presented.Test ProcedurdThe tests were made at a dynsmlc pressure of 13 pounds per squarefoot, which corresponds to a velocity of about 71 miles per hour underStendard conditionsa71 The effective Reynolds number for maximum liftcoefficients for these tests was approximate

3、ly 2. x 106. (EffectIveReynolds nunber = test Reynolds nmiber X turbulence factor. The turblence factor for the Langley 4- by 6-foot vertical tunnel 1s 1.93.)The aiMoil xnodslwhen mmnted in the tunnel completely spanned thetest section. With this type of inetsllatlon,twnefciml flow 1sapproximated en

4、d sectjon characteristics of the -1 can be determined.u.,Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-5Tests of the 0.25c flap used independentlywere made with the O.m flapstrapped at zero defIection end its gap f aired to the airfoil centour. Tor

5、ths tests of the O. flap used independently,the 0.250 flap was strappedat zero deflection and its gap fad to the airfoil contour. Tests ofthe 0.250.flap and the O.m flap used Independentlywere made through aflap.deflection range of 30 with gap seeled but unfalred and through arange of 10 for open ga

6、p.Tests of the flaps in ccmibinationrestrained by strain S to the mainby strain gages to the O. flap. hmomnt readings could be made for eachwere made wfth the O. flapairfoil and the 0.250 flap restrainedthis manner, simultaneous hinge-flap. The parameter ch2b= was“50obtained by setting the 0.250 fla

7、p to zero deflection and deflecting the0.500 flap through a range of 10 with hinge+mmt readings recorded forboth flaps. The parzumer =%0625 was obtained in a like manner bydeflecti.ngthe O.25c flap through a range of 10 tith the O. flap setat zero deflection. These tests were made with open end with

8、 sealed gaps.All tests were made through the f+ttack range fmm zero tonegatfve stall and from zero to positive stall.CorrectionsAn experimentally determined tunnel correction was applied to thelifta71 The angle of attack and hinge momnts were corrected for the effectof streamline curvature induced b

9、y the tunnel wells in accordance with atheoretical.analysisspellmodels.The tunnel+allfor the 0.250 flap,similar to that presented in reference k for finite-correctim were applied in the following manner:a =ao ?r (+o.21czT - 0.160lT)fCh=c % + 0.CM676C2Tfor the 0.50c flap,ao =a % (+ 0.21CZT -0.07602)f

10、Ch . c% + o.00876C%Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-6and for both the 0.25c and O.jOcflaps,wherea.TclTc2Tfc%., .965- 10*WTI)%TNACA TN NO. 1517.masured angle of attackmeasured lift coefficientmqmred lift-inefficient incremmt caused by f

11、lap deflection40)(msasured arbitrarily at a =ormeasured hinge nt coefficientDISCUSSIONThe O.25c and O.50c Plain Flaps Tested IndependentlyLift.The liftcharacteristicsfor the 0.25c flau are wesented in.figw%for open gap and figure 3 for sealed gap. Th li.ft-characteistics for the O.50c flap are prese

12、nted in f -.oop -.0120-.0121 -.0148-.75 -,0123 -.0155TABLE II. FwMmERs Fmo.25cmo.5ccu FIAP6TESPEDIIVWMBIUATIOH W AH I?ACAOOOSIAIRFOILoEp 01Cla 8= %y %e 50 aba5 C$ %29 c% C*625 258%O.oqk 0.0890.0390.0584.43 a.a -o.oq2a. 0119-0.“IJ.O-0a71o141-0.OZ02-0.(x%6SOhd .093 .045 .066 -.49 -.72 -.0068 -.0120 -,

13、0108 -.0144 -.0208 -.oo60a!?! I?=Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . -.=-.-.-= . .S-.z-s.-.=m.s.= = . =- - . - - - - - - _-=.rm.z.*. -s- ,-.- - .-Hinge axis for 0.50 chord flap - -.-. -=- . s-. =a=- . .- . . . . * -. - -. -. .=. . . .

14、 . . . . . . . .- . - Hinge axis for 0.25 cho;d flap - -_- O.CX?5c gapsFigure -plainn *I- -1 7section A-A Details of /VACA 0009 model withflapa.I-JNJz(225c and .soc pGs.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN No. 1517 13 .L?/.0.8.6.4.

15、2oa71-1.0-/2 “-20 -/6 -/2 -8 -4 0 4 8 /2 /6Angle of attack,o(O, deg.Figure 2 .- Aerodynamic section characteristicsof an NACA (7009 airfoil with a 0.25c plain fiapand 0.005c gap.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-14 NACA TN No. 1517.16,/

16、2IIo.04-.08./2.-20 -/6 -/2 -8 -4 (3 4 8 /2 /6Ang/e of attack ,aO, dgFigure Z.- Cmc/uded.20Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA.a71.:-LTN ISO.1517 -/4/2/.0.8.6.4.20-.2-.4-.6-.8-/.0-1.2I-=? /E /-20 -/6 -12 -8 -4 0 4 8 12 16Angk of. atta

17、c k , m., deg15Figure 3.- Aerodynamic section characteristicsof an IVACA 0009 ajrfoil with a 0.25 c phin flapand sealed uao.41Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN No. 1517.a71.Provided by IHSNot for ResaleNo reproduction or network

18、ing permitted without license from IHS-,-,-NACA TN No. 1517./.2/.0.8.6.4.20-.2-.4-.6:8-/.0-20 -16 -12 -8 4 0 4 8 12 i6Ang) of aftack ,m. , -200.-gaps, 0.005 C .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN No. 1517 23a71a15.040-.04g -.08cz-

19、/6 -/2 -8 -4 0 4 8 /2 16Ang/ of attack,OCo,dgFigure 7.- Con f-inued.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-24 . . - -.20.16/2736NAGA .LWNO. 1517a711 1 I I I I I I I I I I I I I I , 1 1 1 I I I I I, I I Ii I1 1 I1 1. I?kktM.(”:)El1 I )%1 I 1

20、I1 w I III1 IiEEEE13%Ilfilllblllm 1 /* 1 I I y 1 w Ii 1 , , 1 1 I I iItttt-Hiilllll Jilll-/6 -/2 .-8 -4 0 4 gap:, 0. Oosc.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-26 NACA TN No. 1517.16./2.08.04c)-.04-.08+246.20-/6 -/2 -8 -4 0 4 8 12 16Angle o

21、fattack, oo, cieg.)Figure 8 .- Continued . .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN No. 1517.20.08.(M$ -.04%$ -.08:28? I 1 L1 1 I # 1 I I 1I 1-/6 -12-8-40481216Angle of attack, m. ,degFigur 8.- Cone/uded .Provided by IHSNot for Resale

22、No reproduction or networking permitted without license from IHS-,-,-28 NACA TN NO. 1517.8.6.4.2072-.4-.6:8-/.0a71a15-/6 -12-B -048/2Angle ofattuck, OCO,degFkjur-e 9.- ffec of deflecting the 025c flap “- “ ,on the aerodynamic section characteristicsof an tVACA 0009 atrfoil having a 0.25c and .a 050c

23、 plain flap . fs = OO;gaps,sold.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.NACA TN No. 1517 -6./2.08.040-04.708-.12.-16/6-/2 -6? -404812Angleoa?+acli,., deg. Figure 9.- Cmtimai .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-