NASA NACA-TN-1110-1946 Two-dimensional wind-tunnel investigation of an approximately 14-percent-thick NACA 66-series-type airfoil section with a double slotted flap《带有双开缝襟翼且大约厚度为14.pdf

《NASA NACA-TN-1110-1946 Two-dimensional wind-tunnel investigation of an approximately 14-percent-thick NACA 66-series-type airfoil section with a double slotted flap《带有双开缝襟翼且大约厚度为14.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-TN-1110-1946 Two-dimensional wind-tunnel investigation of an approximately 14-percent-thick NACA 66-series-type airfoil section with a double slotted flap《带有双开缝襟翼且大约厚度为14.pdf（37页珍藏版）》请在麦多课文档分享上搜索。

1、-. NATIONAL ADVISORY COMMITTEE -FORAERONAUTICS - -TECHNICAL NOTENOO 1110TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF AN APPROXIMATELY14-PERCENT-THICK NACA 66-SERIES-TYPE AIRFOIL SECTIONWITH A DOUBLE SLOTTED FLAP By Albert L. Braslow and Laurence K. Loftin, Jr.Langley Memorial Aeronautical Laboratory

2、Langley Field, Va.WashingtonAugust 1946 _* ._NACALI,BRARLANGLEYMEMOW AERONAUTICLawkyHeldva._.Provided by IHS Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-.- -.j NATIONAL ADVISRY CCWNITTEEFCBAEl?07FAUTICS.s TZCENICAL NOTE NOe 1110“k.4“.a713J.I.-pEwE3iT-T*ficK NAc

3、A 66-sEFIEs-TyPE AIRFOILWITH A 1)01BLJ2SLOTTED FLAP. .APPFK)XIMATELY-. _-SECTION.By Albert L. Braslow and Laurence K. Loftin, Jr.A two-dimensional wind-tunnel invstigation was madefor the purpose f developing a suitable double slottedflap on an aroximatel l-percet-thickm odffied ._NACA 66-series-tyn

4、e airfoil section. Section aerdjnatio characteristics of the airfoil with various double+lotted-flap arrangements are gresented. ._-.-_A maxirum section lift coefficient of 3.0 was obtained -for a 55 deflection of a flap arrangement employlag a0.085-airfoil-hrd vane (vane 4.). The lift caeffictentso

5、btained for flap configurations witlnvane 4 generallywere higher than those obtained with the other vanes testedand viereless sensitive to changes in vane position-ari- “”deflection. Standard airfoil leing-edge Touness! G%iiZ%dapproximately the ss.xedecrement in rntiium section lift coefficient for

6、the airfcil with the fiap deected jOOas for the airfoil with the flan retracted. Differitvalues of the w.aximunsection lift coef$ici-entwere obtained._at high flag deflections when theanRls of tittack”-t-“Mhichthe t;st wa begun was not sufficiently low tointtis.1air-flow separation. INTRCJDUCTIONgre

7、vent .“ _ ._ _ Tests were made in the Laley two-dimensional low-turbulence tunnels of an airfoil section equipped with adouble slotted flap designed for agpl:cat.ionto a fighte-r- “te airplane. ._preliminary desigu of the airplane _indicated that a maximum. section lift coefficient of - .-agproxiwat

8、ely 3.00 was necessary if the airplane were-to ._.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.2 NACA TN NO. 1110have the specified landing and take-off characteristics,Ihepurpose of this i.nvestigatioawas t.odevc.1.opa suit-able double-slotted-f

9、lap confLgurEiti.oilfor usc on thisairplane, The tests were made of a 2).+-inCh-ChQrdmodel of anintermediate airfoil section formed by a strait-linefafrin between a modiiiedNACA 66(215)-211root section;:3:“2$:$36:29J3 m;25.TO17.9011.614.51.2.391.63“. TABIE v TABLE VIoRDINATES OF VANB 5ORDA!CESOFVANE

10、4tati.oneand ordlnatea given inperoent van? almkd. tations and ordinates given inpement vane ohoUpper Sumacwistationo1.3.5.2.70reface LowerSurfaue LowersurraoeOrdiilate Ordinatf8.I.I.3:29?2?:23.63; ;33 .3130. 0.31.6031.7031. OS2 .5J3?2.2J?J11:896.4g2.701.40Stationo1.352.70z:4J.10.8I.13.1z20.527.01i?

11、;3*790= 5$8:00.816.z 3?8 a718=:%J9 ;:100.00Ordinat($;1:2?0.32.251.353.11?:%lg.g13: 1713. 813.24%: p:. 5-.a71. . 100.QONATIONAl ADVISORYCOMMITTEEFOQASROMAUTKS-“ .,Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-14. . NACA TN No. 1110*TABLE VIIORDINATE

12、S OF VA 6 ,tations and ordinates given inpercent airfoil chordUpper Surface Mwer Surfacetat ion Ordinate Stat ion Ordinateo12. 0?2 o18.w:?3 ;:g$ M 3 5.005.00 5.00 2.85J.: 25.69 J: 1.53027.70 .6512:50 29.32 12:50 .30”8.7532,25 18.75 .6325.00 34.20 25.00 1.753+*;gi35.29 31.25 3.1535.80 7.5052% iy t5.0

13、03 6152:53 ,7.226.25 ;1:g 6.2?59.0010.22.50 28.75 2.50 10.8368a71 83 25.30159 21.25 :;:83 10:ga1.25 :;:g 1.25 84387.50 87a71 50 5:283:8 m $g sroen:c), (percentc)1 1 78a7100 I 2s4s3 1 78.54 2.043 2 77*71 1.884 14 78.54 2.7524 78.832.7ii78.0 2.34 77.75 L.884 1.% o4 z 76.9676.88 1.424 7 77.63 2.505 I 1

14、 I 77.83 I 2.176 1 76.83 1.72 77.25 1. 4: 76.51+ L836 : 75*75 2.0876.00 1.4.22 z 77.25 1.58Angle between vanetangent line andairfoil chordllne,?(deg*52,551.0M*5I:Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-,.a71. .NACA TN No. “111O.06 Vane 1Vane

15、3. .Fig. 2- “ “-. - -.Vane chord lineVane-ohord lineL=Y-=-. .0,54-4Vane4 .+- .0771C-?+Vane 5Vane ohord line.-i1 Inoht- -. Vane chord line. NATIONAL ADVISORYCOMMITTEEFOR AERONAUTICSFigure 2.- Sketchesof the five vanesused on the 24-inch-chorddoubleslottedtlapmodel.Provided by IHSNot for ResaleNo repr

16、oduction or networking permitted without license from IHS-,-,-85.1# piment c -+L.13.Airfoil chord lineE+ C+D+m.wUpper 11PlzzoNATIONAL APVISORYCo?M1l-m m AEROMUTKS Figure 3, - various pivot points employed for tests of the double.1-0slotted flap.“. .,.-) ,., , ,: ,.IProvided by IHSNot for ResaleNo re

17、production or networking permitted without license from IHS-,-,-.- .,.” t., . .z!D1-1-1-0I,.*Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . ,. ,., . .,iProvided by IHSNot for ResaleNo reproduction or networking permitted without license from I

18、HS-,-,-. t“ . . . . .w /7/T,., .-:1A ,T.E.0 . -. $-50-55A 55NATIONALADVISORYCONMITTEE m AEUOMNTJCSFigure 6.- Sketch of the double slottd flap.IVane 1, ,confimntion 1, pivot point A.I,.5c1t-z0alIProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-“(d n=2.

19、3xlL+. t-b). =*, i,- , ,. .,. “,. -.,?. i“ ,IProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-,.”I*., . .II. #“, I chord line(d:g) - “(a) Conflfs-tion 2, pivot point A.iJ-m,(b) ConSratlon 1, deflection 50,pivot point A.NATIONAL ADVISORYCoMMn-m m AEnom

20、mcsFigure 8.- Varioua arrangements sf the aouble Blotted flap tested with vane 3.fII IProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1“. .,:i, , 1,I. . .I. . . . .1 ,Provided by IHSNot for ResaleNo reproduction or networking permitted without licens

21、e from IHS-,-,-.“, 1“ .“. .”.I. . . . .Figure 10.- pitotig+aomant oharaoterintlos of an approxhately l nne 3,oonfigumtion 2, p%vot point A; R=8 x106; tests-,TDT713 andns.z0.1-I-JProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-VUIO L piv.t petit n; E

22、E 2.3 x wC; tosw, L= 362md 365.1i; a71 ,I1:, . ., IP1-0ma.“Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-!L-(a) Vane 5,deflection “cotilguratlon 1,500, pivot poht h. NATIONAL ADVISORYCwmTEE m AERmAuTlcsii=P-T-E”“ “-(d:g) ,-50“55 , (b) Vane 6, confi

23、guration 1, pivot point C. f!i=-;! ) . 1. t,(c) vane 6, oonfiguraton I, “,pivot point E. 4Figure 13.- Varioua arrangement of the double slotted flap teated with vanes and 6. x-. . ,. .1,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-“t *“ “ . . . a71 a15 a15a15 a15(a) ml, 5,Cumriablml. (b mIa6, t 1Elzzo.1-P1-0%11-ml.bmProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-