NASA NACA-ACR-3G20-1943 Wind-tunnel investigation of control-surface characteristics XIII - various flap overhangs used with a 30-percent-chord flap in an NACA 66-009 airfoil《对操纵面特.pdf

《NASA NACA-ACR-3G20-1943 Wind-tunnel investigation of control-surface characteristics XIII - various flap overhangs used with a 30-percent-chord flap in an NACA 66-009 airfoil《对操纵面特.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-ACR-3G20-1943 Wind-tunnel investigation of control-surface characteristics XIII - various flap overhangs used with a 30-percent-chord flap in an NACA 66-009 airfoil《对操纵面特.pdf（30页珍藏版）》请在麦多课文档分享上搜索。

1、.$-, - ., , . .+ ACR MO. 3G2011II,NATIONAim ADVISORY COMMITTEE FOR AERONAUTICS/WAlmm Ium)lrrORIGINALLYISSUEDJuly 1943aEA”:. -: . .-.:- . ,.l,-:.- -+: .-:,.L:,:.yv-= . : - . ., .-. s- .,:,.“,. ,.1. - , . ,. ., .” . ,-, ,.,-:,.,.:,. . .,., . .- . . . . .Provided by IHSNot for ResaleNo reproduction or

2、networking permitted without license from IHS-,-,-5Ipfain flap has an overhang of 0.113cf hut this amount ofoverhang does not contribute any aerodynamic lalance.PrecisionThe accuracy of the lift and pitching-moment data isindicated ly the variation in lift andcoefficients at an angle of attack of Og

3、itching-momentand a flap de.flection of 0 among the tests with various overhangs andgap conditions. The maximum error in effective angle ofattack appears to be *0.2. The small amount of positivelift obtained at 0 angle of attack for all tests withflap neutral indicates some inaccuracy in model const

4、ruo-tio or installation. Flap deflections were set within*0.2 at small deflections At the high deflections theangular displacement of.ths flap under load slightly ex-ceeded this value. Tab deflections were set to within*l,5. Tunnel corrections experimetally determined inthe NACA 4- by 6-foot vertica

5、l tunnel were applied only tolift. The hinge moments are probably slightly higher thanwould be obtained in free air and, consequently, the val-ues presented are consiered conservative. The incrementsof profile-drag coefficient are believed to be accuratewithin *0.001 for snail flap deflections and w

6、ithin *0.003for large flap deflections and should be rea-sonally inde-pendent of tunnel effect, although the absolute value issubject to an unknown correction. Inaccuracies in thesection data presented are thought to Ye negligible rela-tive to inaccuracies that vill be incurred in the appli-cation o

7、f the data to finite airfoils.Presentation ,of DataThe aerodynamic section caracteristicg of the NACA66-009 airfoil with a 0.30c flap are presented in figures2 to 7. The effect f flap deflection on the characteris-tics is shown in figure 2 for the plain flap, in figure 3for the flap with a 0.35cf ov

8、erhang? and in figure 4 forthe flap with a 0.50cf overhang. Tigures 2(a), s(a), and4(a) show the results for the sealed-gap condition andfigures 2(b), 3(b), and 4(b) for a gap of 00005c at theflap nose. Tigures 5, 6, and 7show the effect of tab de-flation on the characteristics of the airfoil with t

9、heplain flap? the flap with a 0.35cf overhang, and the flapwith a 0.50cf overhangr respectively. .Figure 5(a) showsthe effect of tab deflection” with tho flap neutral; figureProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-bj(b),withthe flap defleoted

10、 10; and figure (c), withthe flap deflected 20.Increments of profile+irag coefficient caused by flapdeflection are shown in figure 8 for the three flap ar-rangements tested. The incrementswere obtainedby sub-tracting the drag for the flap-neutral condition at anglesof attack of -4, 0, and 4 frcm the

11、 drag for the flap-deflectedcondition at theThe data far the NACAwith the data for theICAto k andwith the data forreferences 6 to 8.seineangles of attack.6QOg airfoil are comparedOOQ9 airfoil from referencesthe NACA 001 airfoil fromDISCUSSION OF AIROIUNAMT.CSECTION. . .LiftApparently the nature of t

12、he air609 airfoil is different from thatc13ARAcTERImIcsflowoverandNACA 001 airfoils as videncedby theof the lift curves of figures 23 3, and 4.overtheNACAthe NACA 0009nogl.inearitySeparationI1seems to begin at batherlow angl thedecreasewas greaterforthe largeroverhangs.The testsandthe discussioninre

13、ference5 showedthattheairfoilandflapcharacteristicscouldbe changedby modifyingthethiclmessand shapeof theairfoilsur-facenearthetrailingedge. Decreasingtheanglebetweenthetwo surfacesat thetrailingedgewillalterthepres-euredistributionsoas to increasethe liftovertherearportionof theairfoil. Thus,thegre

14、aterlif%urveslopeof theNACA6 whereas %Pf+l, therefore this curve was notused in measuring (achfaf)uo,. “ . -.i. - -:. -.:,:,:. -. ,: .: , ;.,.-T-7,- .- .“ . -. : ., .!,= . , . . . _. ”*-.-.:”i.-.-.- “: - :-,-,-:.,:,:. ,-.,/-, .-.,-. . A . .Provided by IHSNot for ResaleNo reproduction or networking p

15、ermitted without license from IHS-,-,-9Xxcept for the 0.50cf overhang with sealed gap thehinge-moment parameters were more negative for the HACA66-009 airfoil than for the ITACA 0009 and NACA 0015 air-foils with similar flap overhangs. Some overbalance oc-curred vith the 0.50cf overhang with both se

16、aled and un-sealed gap. Tor all conditions tested with the 0.35cfand 0.50cf overhangc the maximum negative value of(acf/atf) occurred at zero flap deflection. Theo,G. .,variation in slope over the low deflection range “may beimportant in considering the control-free stability of theairplane. The inc

17、read effectiveness of the balance atlarge deflections is probably caused by the high velocityover the nose of the halanc-e as it protrudes from the air-foil surface. Although no tests vere made at flap def-lections smaller than 5 on the flas with large over-hangs on the iTACA 00G9 and NACA 0015 airf

18、oils, the de-creased effectiveness of the balance was evident even at5 deflection and would probably le mora evident at smallerdeflections, es on the N.4 ,.,.,. .;: . :.,- ”.,-%:., ,-,. .-.:s;.:. a . “. -,.“ .5 .,.,a71i1Provided by IHSNot for ResaleNo reproduction or networking permitted without lic

19、ense from IHS-,-,-I!15I,.I“TABLE IORDINATES FOR iTACA 66-009 AIRFOILStations and ordinatee in percent of airfoil chordStationo.50.751.252.557.510 “1520 “253035 “4045505560.65.707580859095100100Ordinateo.?0.841.051.411.942.342.673.193.59“ 3.914.164.334*444.504.494*()4.21 ,3.913,462.842.221.60.92.37(

20、.10)oL.E. radius: 0.558.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABMIIPR VALUES FOR0.300BLUNT-NOSEFLAP WITH THREE OVERHANGSh) A 0.200f PLAIN TAB ON AN NACA 66-CKJ9AIRFOILoept 8Snoted!mthetext,theparameterslistedwereme8suredoverssmallrangeofan

21、glesofattaokandflapdefleotlonswheretheourvesaremorenearly linear. Becaueeofthegeneralnonlinearityoftheourvea,however,theparameterelxmldnotbeusedwithoutreferenoetof.2 toVd)hhf, Of,otI+%)b ol#6-0.67-.56-.59-.62-.61-.66)Om)6f,6t )bOm IWt ,)133b6t ae,t-0.010-.008-.008)bCht, 6f,-0.004-.006-.0080.l130f(Pl

22、ainrlai)Oapenealed 0.102(lapunsealed .095-0.013-,008-.008-0.180-.180-.167-.180-.175-.180-0.0074-.00830045-.00700-.0008-0.0120-.0128-.0060-.00660-.00140.00600-.0010-.008-0.16-.r.15-.16).360fOaps oealed .099(lapsunsealed .087).soof13apssaled .102asunsealed .081L-3J4 ,L . - .Provided by IHS Not for Res

23、aleNo reproduction or networking permitted without license from IHS-,-,- . _i,!.:.-.,;:.; l;,./.,“i.,I.,:!.4,:. ,.1“!.0.50C+ Overhang -A /rfo/ contourto flop vase ruw+ C=Z4,(1I “!NACA Fig. 2btI I I I i I I I-fm,;1I1Ii “klAcA .12i! :/6:20- .040-32+ 44 .20 .2.46.8 10 “L2 L4 L6 L8 20 22.(c)af=zo”Figure

24、 K-Cone/udf/apgap-O.005c; fobgup-0./c;8,=0:Fig. 7.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- . . . . . _ . _. .L-3U., I 0 “5 10 /.55 Q 5 /0 ,/5 .05/0/5) figure 8. -Incre ent of airfoil section pmfik-dq coe jcient caued by/P fdefkc ton of a L!30 c flop wtth blunt nose an three overhangsand with sealed ond 0.005c 9c2p.*. .-n$a)Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-