NASA NACA-RM-L53D17-1953 Wind-tunnel investigation at high subsonic speeds of a spoiler-slot-deflector combination on an NACA 65A006 wing with quarter-chord line swept back 32 6 de.pdf

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1、SECURITY INFORMATION+r-(A),_. .c. -.=. , .RESEARCH MEMORANDUMWIND -TUNNEL INVESTIGATION AT HIGH SUBSONIC SPEEDS OFA SPOILER-SLOT-DEFLECTOR COMBINATION ON ANNACA 65AO06WING WITH QUARTER-CHORDLINE SWE.PT BACK 32.6By Rapmn.d D.VoglerLangleyAeronauticalIkboratoryhlY Field,VascIAmnmLlDocuMEmNATIONAL ADVI

2、SORY COMMITTEEFOR AERONAUTICSWASHINGTONMay 29,1953 RECEIPT SIC! ”-uREEQUiProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TECH LIBRARY KAFB, NMNACA RM L53D17NATIGNAL ADVISORYC!OWIITIJRFOR AERONAUTICS.,RESEARCH MEM3UMDUM .WIND-TUNNELINVESTIGATIONAT HIG

3、HSUBSONICSpEIX)SOFA SPOILEI1-SLOT-lIWcTORCOMBINATIOIJONMiNACA 65AO06 WING WITH WARTER-CHORDLINE SWEPI BACK 32.60By Raymond D. VoglerSUMM4RYAn investigationwas made in the Langley high-speed 7-by 10-foottunnel through a Mach number range from 0.4 to 0.91to determine thelateral control characteristics

4、of a wing-fuselage combination with thewing qurter-chord line swept back 32.60, an aspect ratio of 4, a taper. ratio of 0.6,and an NACA 6AO06 section. One wing panel was equippedwith a 50-percent-semispan inboard spoiler-slot-deflectorcombinationlocated between the 55-and 70-percent-chord lines. *As

5、 was previously found at low speed, the loss in rolling-momenteffectiveness of an unvented spoiler at high wing angles of attack ismaterially reduced by the incorporation of a slot and deflector at Machnumbers up to 0.91. The optimum ratio of deflector to spoiler projec-tion for best results varied

6、with angle of attack, but a ratio of three-fourths to one gave appreciable roQing-moment effectiveness through theangle-of-attack range from O” to 20”.INTRODUCTIONThe spoiler used as a lateral-control device has been the subjectof considerable investigation at low and high speeds, and on both swepta

7、nd unswept wings. Recent investigations of spoilers used as lateral-control devices have shown that on thin wings with small leading-edgeradii the unvented spoiler loses effectiveness rapM1.y as the angle ofattack is increased above about 8 (ref. 1). References 2 and 3 have?shown that this loss in e

8、ffectiveness at the higher angles of attackcould be reduced by using a slot in the wing behind the spoiler thatallowed the air to flow through the wing from the lower to the upper.surface when the spoiler was deflected.=Provided by IHSNot for ResaleNo reproduction or networking permitted without lic

9、ense from IHS-,-,-2 NACA RML53D17The purpose of this investigationwas to determine whether a slot .4plus a deflector is as effective at high subsonic speeds as it was atlow speeds (refs. 2 and 4), and if so, to determine the ratio of deflec-tor projection to spoiler projection for most benefici-alre

10、sults. The .Investigationwas conducted in the Langley high-speed7-by 10-foottunnel through a Mach number range from 0.4 to 0.91 d at an angle-of-attack range from 0 to 20 except when limited by tunnel operating con-ditions. Rolling and yawing moments were obtained wit_hspoiler alone,with slot plus d

11、eflector, and with spoiler-slot-deflectorcombination.Lift, drag, and pitching moments of the model were also obtained for .the spoiler-slot-deflectorcombination. .-SYMBOLS AND COEFFICIENTSThe forces and moments measured on the model are presented aboutan orthogonal system of axes. The longitudinal a

12、xis was parallel tothe free-stream air flow and the vertical axis was in the vertical planeof symmetry. The origin of the axes was in the plane of symmet at alongitudinal position corresponding to the projection_of the quarter-chord point of the mean aerodynamic chord (fig. 1). .CL lift coefficient

13、(Lift/qS) Cal drag coefficient (Drag/qS) .cm pitching-moment coefficient (Pitchingmome/qS=)cl rolling-moment coefficient resulting from spoiler and/ordeflector projection (Rollingmoment/qSb)Cn yawing-moment coefficient resulting from spoiler and/ordeflector projection (Yawingmoment/qSb)dynamic press

14、ure) pounds per square foot ()PV2 -TP mass density of air, slugs/cu ft v free-stream air velocity, fpss wing area, 2.25sq ft .1-b wing span, 3.0 ftc local chord, ftE mean aerodynamic chord of wing, 0.765ftvm#or (;ef. 2). Figure 4 shows the effect a deflector hinged at the 70=percent-chord line, and

15、a slot in the wing between the tw hinge lines. Thespan of the controlswas 50percent of the wing semispan and the con-trol was located inboard on the right wing. As a result of the inves-tigation the following conclusionsare made:1. As was previously found at low speeds, a spoiler-slot-deflectorcombi

16、nation is effective in producing rolling mmnents over a greaterangle-of-attackrange than an unvented spoiler alone at Wch numbers _up to 0.91.2. The optimum ratio of deflector projection to spoiler projectionfor rolling-momenteffectivenessvaries with angle of attack, but aratio of 0.75 to 1.0 gives

17、appreciable effectivenessthrough the mgle-”of-attack range from 0 to 20.3.A deflector and slot without a spoiler is also effective inproducing rolling moments at high angles of.attack. .1!.Langl Aeronautical Laboratory,National Advisory Committee for Aeronautics,Langley Field, Va.Provided by IHSNot

18、for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RML53D17 7REFERENas1. Vogler, Raymond D.: Wind-Tunnel Investigation at High SubsonicSpeeds of Spoilers of Large Projection on EUINACA 65AO06 WingWith Quarter-ChordLine Swept Back 32.60. NACA RML5U1O, 1952.2. Watson,

19、Janes M.: Low-Speed Lateral-Control Investigation of aFlap-Type Spoiler Aileron With and Without a Deflector and Sloton a 6-Percent-Thick,Tapered, 45Sweptback Wing of AspectRatio 4. NACARML52G1O, 1952.3.%mnondj Alexander D., and Watson, James M.: Laterl-ControlInvestigation at Trsnsonic Speeds of Re

20、tractable Spoiler andPlug-Type Spoiler-SlotAilerons on a Tapered 60 Sweptback Wing ofAspect Ratio 2. Transonic-Bump Method. NACARML5m_6, 1952.4. Wenzinger, Carl J., and Rogallo, Francis M.: Wind-Tunnel Investiga-tion of Spoiler, Deflector, and Slot Lateral-Control Devices onWings With Full-span Spli

21、t and Slotted Flaps. NACA Rep. 706, 1941.5.Gill-is,Chrence L., Polhsmus, Edward C., and Gray, Joseph L., Jr.:Charts for Determining Jet-Boundary Corrections for CompleteModels in 7- by 10-Foot Closed Rectangular Wind Tunnels. NACAWR L-123, 1945. (FormerlyNACA ARR L5G31.)6.Herriot, JohnG.: Blockage C

22、orrections for Three-Dimensional-FlowClosed-ThroatWind Tunnels, With Consideration of the Effect ofCompressibility. NACA Rep. 995,1950. (SupersedesNACARMA7B28. )41Ek%amiimProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-8Wing DataAmAspect fVtiOToPer m

23、tioNACA RM L53D1745?2 32#sqin4?0 /77-om.,1.6Section A!ACA 65AO06Spon 36.OinRoot chord l/25inTip chord 6.75in +Quarter -cfwdsweepbuck 326 30.0A II dimensions in inches uSections A-A_ Ploin wing j8*=0, LA /0 :n /2.5 o-4 0 4 8 /2 /6 20 24Q, deg(a) M=O.40.Figure 3.-Variation of lateral control character

24、isticswith angle ofattack for various projections of the spoiler alone with slot closed.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM L53D17.11.04.(22Co-.02.02 7.5/0.02 “Cn o-.02 -4 0 4 8 /2 /6 20 24a, deg(a) M =0.Figure h.-,Variation of la

25、teral control characteristicswith angle ofattack for various proections of the deflector with_slot open endspoiler off. .a71Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM L53D17 13.04.02o.020 off 2.5a75 off 50 off Z5A off 10.02c o-.02-4 0 4

26、8 /2 /6 20d?,deg(b) M=o.85.Figure 4.- Concluded.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACARM L53D17.04.020-.02-.02c“ o-m05 23055A5 Z5A 25 2;5-4 0 4 8 /2 /6 20 24CY,dega71a15.(a) M= O.40.Figure 5.- Variation of lateral control characteristic

27、swith angle ofattack for various projections of the spoiler-slot-deflectorcombination.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACARM L53D17 158.04.020.02c“ O-.02f?“-8S(percento 10a75 /0o /0A/0n 258chord)2.557.5/0Z5-4 0 4(a) M =Figure8 /2 /6 2

28、0 24a, aeg0.40. Concluded.5.- Continued.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-16,04.02o-.02.02c o-.02 rNACA RM L53D17.-& ad(percent chord)05 2.505 5A5 Z5A25 2.5-4 0 4 8 /2 /6 20a, deg(b) M =0.Figure 5.-Continued.P.a71.cProvided by IHSNot fo

29、r ResaleNo reproduction or networking permitted without license from IHS-,-,-3Y lUCARM L53D17 17.Cz.06.04.02+ ad(pefcent chore).02c 0-.02T I-4 Q 4 8 /2 16 20. a, deg(b) M = 0.85. Concluded.Figure 5.- Concluded.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from

30、IHS-,-,-NACARM L53D17./c. o-./20/6/2a)g 840-4-05Q5 7.5Von /0&4.3.2 CD,/o-4 -.2 0 .2 4 .6 .8 /.0(a) M= O.kO.Figure 6.-Effect of spoiler and deflector projections with slot openon the aerodynamic characteristicsin pitch.cmProvided by IHSNot for ResaleNo reproduction or networking permitted without lic

31、ense from IHS-,-,-NACARM L53D17 -./C* o-./20/6/2ff,deg840-4n5 75VD.3.2CD./o(b) M = O.Fi 6.-Concluded.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-lWA RML53D17M 40-.85*-0 4 8 /2 /6aaegFigure 7.-Ratio of drag snd roUing-moment coefficients of spoile

32、r-slot-deflector combination to that of spoiler alone at vagious wing anglesof attack. 6s = -10 percent chord, 8 = 7.5 percent chord.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-lUC!ARM L53D17 21.02-.02.04c“ .02(?.M= .40M= .80hf=.85M.9/ - no 2 4 6

33、 8.04.02 Czc?o (de00a75 4A8o /2V /6n 20.048d, ?fcefCM(a) b. = -5 percent chord.Figure 8.-Effect on the rolling-moment coefficient of various ratios of.deflector proection to spoiler proection for the spoiler-slot-deflector combination at various wing angles of attack.Provided by IHSNot for ResaleNo

34、reproduction or networking permitted without license from IHS-,-,-22 NACA RM L53D17.04.020-.02.04Cz .0.201 I I 1 I I I I I I I0 2 4 6 8(b) b = -10Figure 8.-percent chord.Continued./0-.-ds.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I?ACARM L53D17

35、 23.06.04c.02.06.04.0260 2 4 6 8 10, percent chod(b) b = -10 percent chord. Concluded.Figure 8.-Concluded.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-24 lUICARML53D17.04.020. fw.W&.?04M=B5o-.02.-/0 -8 -6 -4 -2 0,percent ChrdFi&ue 9.-Variation of rolling-moment coefficientwith conibinedprojec-tions of deflector and spoiler in 1.0 to 1.0 tio for the spoiler- a71slot-deflector conibination.5s = bd.NAcA-Laney .6-2Q-tj3 -ssProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-