NASA NACA-RM-L53J21-1953 Wind-tunnel investigation at transonic speeds of a spoiler-slot-deflector combination on an unswept NACA 65A006 wing《在跨音速下 非扫掠NACA 65A006机翼尾翼开缝导流板组合的风洞研究》.pdf

《NASA NACA-RM-L53J21-1953 Wind-tunnel investigation at transonic speeds of a spoiler-slot-deflector combination on an unswept NACA 65A006 wing《在跨音速下 非扫掠NACA 65A006机翼尾翼开缝导流板组合的风洞研究》.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-RM-L53J21-1953 Wind-tunnel investigation at transonic speeds of a spoiler-slot-deflector combination on an unswept NACA 65A006 wing《在跨音速下 非扫掠NACA 65A006机翼尾翼开缝导流板组合的风洞研究》.pdf（29页珍藏版）》请在麦多课文档分享上搜索。

1、.-4.:” “+ SECURITY INFORMATION;# P,#copy RM L53T21RESEARCH MEMORANDUMW-TUNNE L INVESTIGATION AT TRA3JSONICSPEEDS OF ASPOILER-SLOT-DEFLECTOR COMBINATION ON ANuvmm NACA 65AO06WINGBy Raymond D. VoglerLangley Aeronautical LaboratoryLangley Field, Va.cus%lFImMmJhmiTNATIONAL ADVISORY COMMITTEEFOR AERONAUT

2、ICS. - -i,.1WASHINGTON kDecemlxx 8, 1953 .III. . - J, . . .- . - 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-,-,-. .TECH LIBRARY KAFB, NM,HNAC

3、A RM L53J21NATIONAL ADVISORY C FOR- Illlllllluullllulmlll0144282.-.AERONAUTICSRESEARCHmoRANDuMIWIND-TUNNEL INVESTIGATIONAT TRANSONIC SPEEDS OF AEit?OIIJR-SLUl-DEFLECTORCOMBINATION ON ANtnwwEPT NACA 65Ao06 WINGBy Raymond D. VoglerSUMMARYAn investigation was made in the Langley high-speed 7- by 10-foo

4、ttunnel to determine the effectiveness of a spoiler-slot-deflectorcom-bination in producing rolJing moments in the transonic speed range atangles of attack as high as 24. By use of the transonic bump a Machnuder range frm 0.62 to 1.20 was obtained. The wing had an aspectratio of 4, a taper ratio of

5、0.6, an unswept quarter-chord line, andNACA 65AOC% airfoil sections. Forces and moments on the semispan modelwere obtained with a 57-percent-semispanoutboard spoiler-slot-deflectorcombination located between the 55- and iO-percent-chordlines. Forcomparison, data were also obtained with spoiler vente

6、d and unvented andwithout a deflector.As was previously found at lower speeds, a spoiler-slot-deflectorcombinationwas more effective at transonic speeds than a spoiler alonein producing rolJJng moments over a eater angle-of-attack range. Atpositive angles of attack up to about 12 the spoiler and the

7、 spoiler-slot-deflectorcombination suffer some loss in effectiveness in and abovethe.transonic speed range, but at high angles of attack both configura-tions show increasing effectivenesswith,increasingMach number in theregion near M= 1.0. The rollipg effectiveness of the spoiJ_er-slot-deflector com

8、bination is approximately proportional to the projectionfor the range investigated.INTRODUCTIONThe spoiler used as a lateral-control device has been the subjectof considerable investigationat low and high speeds, and on both sweptand unswept wings (refs. 1 to 3). Recent investigations of spoilers us

9、edas lateral-control devices have shown that on thin wings with smalla71 ,._._._Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. .-. . .-.2 NACA RM L33J21leading-edge radii the unvented spoiler loses effectiveness rapidly asthe angle of attack is in

10、creased above 8 (refs. 2 and 3). However,investigations at low and high subsonic speeds as reported in refer-ences 3 to 5 have shown that this loss in effectiveness at the higherangles of attack could be substantially reduced by using a slot.in thewing behind the spoiler that would allow the air to

11、flow through thewing from the lower to the upper surface when the spoiler was deflected.The purpose of this investigationwas to extend through the tran-sonic speed range previous low and high subsonic speed investigationsof spoiler-slut-deflectordevices for lateral control. The investigationwas made

12、 in the Langley high-speed 7- by 10-foot tunnel using”the tran-sonic bump to obtain Mach numbers from 0.62 to 1.20. The angle-of-attackrange was -4 to 24. Rolling, yawing, and pitching mcments, and liftand drag were obtained with spoiler alone, spoiler-gap lip cotiination,and spoiler-slut-deflectorc

13、onibination.SYMBOLS AND COEFFICIENTS. .The forces and moments measured on the model are presented about anorthogonal system of axes whose origin coincides with the point of inter-section of the root chord ltie and the quarter-chordline. The longi-tudinal axis IS parallel to the free air stream and t

14、he lateral axiscoincides with the quarter-chord line.5 lift coefficient,A% increment of liftCD drag coefficient,ACD increment of dragTwice semisDan liftqscoefficient produced by the controlTwice semispan dragqscoefficient produced by the control% pitching-moment coefficient,% increment of pitching-m

15、omentcontrolTwice semispan pitching moment(0.The variation of rolling-moment coefficientwith projection is givenin figure 6 for the spoiler alone and for the spoiler-slot-deflectorcom-bination at 0 and 16 angles of attack. The increased effectiveness ofthe spoiler-slot-deflectorcombinationthrough th

16、e )pojection range atlow and high angles of attack is indcated. The effectiveness of thecontrols”is approximatelyproportional to control projections, slthoughthe spoiler alone has lower effectiveness in the projection”range nearone percent.CONCLUSIONSA wind-tunnel investigationwas made to determine

17、the effectivenessof a spoiler-slot-deflectorcombination in producing rolling moments inthe transonic speed range through an angle-of-attackrange from -4to 24. As a result of the investigationthe following conclusions aremade:1. As was previously found at low and high subsonic speeds, aspoiler-slot-d

18、eflectorcombination is more effective in producing roXlingmoments over a greater angle-of-attackrange than an U.nvented)spoiler aloneat Mach numbers through the transonic range up to 1.20. .2. At positive angles of attack up to about 12 the spoiler and thespoiler-slot-deflectorconibinationsuffer som

19、e loss in effectiveness inand above the transonic speed range, but at high angles of attack bothconfigurations show increasing effectivenesswith increasingMach numberin the region near M = 1.0. “3. At Mach numbers from 0.62 to 1.20 and angles of attack from -4to 24, the rolling effectivenessof the s

20、poiler-slot-deflectorcombina-tion is approximatelyproportional to the projection.Langley AeronauticalLaboratory,National Advisory Committee for Aeronautics,Langley Field, Vs., October 7, 1953. -. - -_. .- .- .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from I

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38、9-.0011.0003.0011-.0113-.0108.0069-.0046-.ooa-.0000.0007IIIwProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Table D, Spoiler, Gop, md LIPM,68.6*.62.6B.ea,60.B4.04.04:8:.84.94.95.9J.95.W5:8!1.011.011.011.011.011.011,011.011.0?1,011.07i,of1.071.011.071

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