NASA NACA-WR-L-464-1942 Wind-tunnel investigation of control-surface characteristics V - the use of a beveled trailing edge to reduce the hinge moment of a control surface《操纵面特性V的风.pdf

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1、-?j.!. ),.ARR Merch 1942-1;/fi /JA-: JNATIONAL ADVISORY COMMITTEE FOR AERONAUTICSWAllrrml lUIPOR!IORIGINALLY SSUEDiMarch 194 asAdvance Restricted ReportWIND-TUNNEL INVESTIGATION OF CCNTROL-SURFACECHARACTERISTICSv- THE USE OF A BEVELED TRAILING EDGE TO REDUCETHE HINGE MOMENT OF A CONTROL SURFACEBy Ro

2、bert T. Jcmes and Milton B. Ames, Jr.Langley Memorial Aeronautical LaboratoryLangley Field.,V, .“,le 110 As ShOWil in f3i?C 2$ the fllp WS.SJ1 of the plain r.n%alanced type9 30 yercent of the airfoil chordin width. The tests were made with. the gap both sealed andopen,The procedure Gf the tests was

3、similr to that followedin reference 1. They were made in the NACA 4-foot by6-footvertical tunnel: modified as described in reference 2. Thelift, the drag, and the pitching moments were measured ona three-compone:t tialance.a71 The hinge moments were measuredelectrically with a ,e;hbated torque rod b

4、uilt into themodel . The model extsr:(ledcompletely across the closedtest section of the tuncelg so that the flow was very nearlyto-.dimensional. The tec+ts were “made ah a dyne.mj.cpressureof 15 pounds per squara foot corresponding to a velocityOf about 1?6mi:l!esper hour and a test Reynolds number

5、. ofl,!),ofio The flap deflection was varied in 5 in;gmentsfrom Oo to 3(J0, In some casss chock pojnts at fromneutral were obtainzdO T!ft, drag$ airfoil pitching moment,and fla:p hicge mometits were measured throughout the anglc-of-aitack rzm.ge, f:in Fcsitive to ngative stall of theairfoil, at 2 j.

6、n.erval Of angle of attack.Precls3.on iThe naximum er=Gr in the angle of attack or in flapsetting appears to be about aaezo An experimentallyd.eterminecl cor:tiection has been a;plied to the lift but notto the hinge moments. The hinge moments are probablysligltly higher than would be otitaiiledin fr

7、ee air. Itshould be nctd thafi the d.zJagOf the basio 0S09 airfoilis somewhat higher than is. obtained in other tests at thesame Ileynold.snumber.Symbolsc1 airfoil section lift coefficient (1/qc)Cd. airfoil section profile-drag coefficient (do/qc)Cm airfoil section pitching-moment coefficient (m/qc2

8、)Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-%Cha.tif2domhcCfcflap section hfnge+nonent coefficient (h/qcf2)angle of attack of infiniteaspect ratioflap angle with respect to airf6ilairfoil section liftairfoil sectionprofile dragairfoil sectionpit

9、ching moment about quarter-chordpon.tof airfoilflap sectionhingemomentchord of airfoil wth fl.psaeutralflsp chardchcrd of beveladportion of flapE+otfcJndata are p?.cttedin figure 4, Figures 7 and.6, CVJ2!i0”kt(_4dfrOT1ih section da.%: for example, a large deree of balance with the.inset-hinge type o

10、f ccntrol surflace requires such a longoverhang that the parcissiblc doflecticn of the tlap islimited. eus of a large horn b%lence introducesstructural difficulties. It i-shelpful$ therefore, toProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-6. .,.Pr

11、ovided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.-.,2. Ames, Milton B. Jr, and Sea.s, Richatd 1.: Pxessure-.Di=tribution Investigation of an N;AC;A CQ09, Afrfoilwith a 30-l?ercent-Chord Plain Flap and Three Tabs.T. N. 0. ?59, N.#.CA,1940.30 Sears, P,ic

12、-lard10: “Tin-Tunel Data bn the AerodynamicChaze,ctei-istics of Airplane Control Surfo.cese NACA Ac3 No.zL08, 19430Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-#Ed.0.mm-c_, - -J-(i. -1Ln.+Pci-P0mCDzC“P. . -. . tProvided by IHSNot for ResaleNo repr

13、oduction or networking permitted without license from IHS-,-,-.9.Sila”k!.ons ordinatesfrom hinge axis) 10l_g4.827.85100,O-J1.5.2.519.7025.1530.00.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . . .-.Modifications“- -FJ-ain *_-”(-1-“_ .L -L.

14、20cf ellipticaljL. _G.Ocf elliptical,)_”-r - 5eI;icircular:-,- _._L-Eulge.- . . ./ da)Imf).,.-0.01.2- .(307- .oo-.003.000-.006-.011-.012-solo.“o.006-.003-.001.oo.002-.003-.008-.009-.005.092.091.090.088.091.099.0950.066.070.080Un-st.a31.e.C68.059.071 .0.001.133.03?3.ck8.051“i%?;)-.-pf,lcz-!) .91-0-.0

15、09-.008- .ofi- .C)C7-.008-.008-.010-.010%25 1 w I . IJ r /111111 1143011 I I I Ib+i f1 /, d, N/YI I4 P b7 / / / o r 0/ LY/ / 42Vf - I-4 /- “/ / /J / /,-8 / ,-0f w/ / d _ _ _ _ _ _ _ _ _ _ _ _ _-12 k/ r.-16 M J 1 “(a)-20- .8 “ -.6 -.4 “-.2 -. . . . .-. 0 “ .2” “ .4” - .6” - - .8 /.0 /.2 /.4- ,-1Provi

16、ded by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-IA“-.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Id“. .-.*=L I -1I I I I .1 I I, IY-.3t.2 H=ltg-. -4keve,O,I+TcfoProvided by IHSNot for ResaleNo reproduc

17、tion or networking permitted without license from IHS-,-,-I1+“.,T r T I 10 01 I I I I I I1:,: 1 ?I I I I I I I I I I I I I I v-l v I /I I I IIi. /5 I I I I 1 I II I I I 10 25 I I I I I I A-1-iIIIFigure 4d.- Trailing-edge bevel, O.10cf.Provided by IHSNot for ResaleNo reproduction or networking permit

18、ted without license from IHS-,-,-. . , Lr 4614. .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . “h. - HIIHT?IProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-*,(c oAD8 bo41+H+1 I I I III I I Iv 20

19、25/-/-/ 1/ - I?/Qo A/i/ ,./.g /- /.d-0 -4 / 7 . / / zo / / / / -8 / / / 5; / / / /l section lift coefficient+, qFig2re 45.- EMlged flap.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Angle of affacfr, a_O,deg,a15 ;“& i c1 a Cb, “111-+-+dlllAirfoil s

20、e cfibn pitching-momentcoe fficien c. Flap secfion.1hirme-moment coefficienf, chI I I v I I l I . ! b. “& I I I I I I lNl n I lProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Iig.51.0.8c.L.4b.p+-+1.6 I y/1 I I .4-!. .I ,/ I t-+-i,./ i-T-I.20,*.,-p-t-

21、 1“r!.- 4 I-+! itI I I i I i I Io 4 /3 12 16Angle of attack, do, dogFire 5,- Typical vari,ations of Zift and h$nge moment with angle ofattack. &f=0.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.b,*1c * 0FiQgu.re G,- 6 12 lE 20 “Flap deflection, f, degical variation:. of lift and hinge moment with flapdeflection. =:Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-