NASA NACA-RM-A51G31-1951 The forces and pressure distribution at subsonic speeds on a plane wing having 45 degrees of sweepback an aspect ratio of 3 and a taper ratio of 0 5《在亚音速下 .pdf

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1、: . :RESEARCH MEhiif$=ANU. w . . . . . i . : * - . .- .* , * TIiE FCRCES AND PRE , . ON A PLANE WING HAVING 45O OF SWEEPRACK; APj ASPECT . . - . : Dv! SPRY COMM t TTEE .a -. . -_ . . : -,- : FOR AERONAUTICS - . ., . _ . . _;. * WASHINGTON . - ,October 16, 1951 Provided by IHSNot for ResaleNo reprodu

2、ction or networking permitted without license from IHS-,-,-. b t NAOA EM A51G3l f J!uTIoFlAL ADmoRY cm FORAERONAUTIGS THEFORGl?SARDPRkSSDREDISCTRfBUTIOAT SUBSORIC SPEEDEj ON A pLlwE WIMG EiAVIRG 45 OF i53mEPmoK, Am ASPECT RATIO OF 3, ABD A TAPER RATIO GF 0.5 By Carl D. Kolbe and Frederick W. Boltz A

3、n investigation was conducted to determine the effects of scale and compressibility on the forces, mmnts, and pressure distrfbution on a wing having an aspect ratio of 3 and a taper ratio of 0.5. The line joining the q,uarte for Mach mmibers ranging from 0.08 to 0.96 at a oonstant Reynolds number of

4、 4,000,OOO; and for Mach numbers of 0.08, 0.25, and 0.60 at a constant Reynolds nmiber of ,OOO,GOO. It was indicated from the force and moment data. that, for all Mach mmibers and Reynolds rumibers in the test range, no apparant flow sepa- ration existed near the leading edge of-the ting for lift co

5、efficfents less than 0.3. At higher lfft coefficients, the initiation of flow sep aration and reattachment near the leading ede of the outer sections of the wing was generally accompanied byL Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-6 NACA RM

6、A51G31 pitching moment at Reynolds numbers of 4,OOO,OGO, ,OOO,OOO, 8,OCKI,OOO, l2,000,000, and B,OGO,OGO for a Mach number of 0.25. Similar measure- ments were made at a Reynolds number of 4,000,OOO for Uach numbers rang- ing from 0.08 to 0.96 and at a Reynolds number of ,OOO,OOO for Mach numbers of

7、 0.08 and 0.60. The angle of attack was varied from -2 to 30 during the Low-speed tests, but this range was reduced at the higher Mach numbers where wind-tunnel power Umitations prevented testing at the higher ang!es of attack. At Reynolds numbers of 12,000,OQO and B,OOO,OCO, the capacfty of the win

8、d-tunnel balance system limited the force measurements to angles of attack of 28O and 160, respectively. Surface pressures on the tunnel wall were measured in the vicinity of the model to ascertain the test conditions at which the data may have been affected by wind-tunnel choking. As an adjunct to

9、the basic tests, an investigation was made to determine the effect of various seals at the model-turntable juncture on the measured forces, moments, and pressures on the model. For each of the SIX axrangements shown in ffgure 4, mea suremes of the IJTt, drag, pitcuw moment, and static pressures on t

10、he wing were obtained for Mach mOOO the onset of separation and reattachment of the flow n000,000, obtained from figure 14(b), are shown to have gradually become more negative with increasing Mach nuniber. At Mach mmibers slightly below those where the Provided by IHSNot for ResaleNo reproduction or

11、 networking permitted without license from IHS-,-,-12 NACA I- The chordwise dietribution of prefleure coefficient at the aeven spar for Mach numbers up to 0.96 at a constant Reynolds number of 4,000,GOO; end for Mach ntiers up to 0.60 at a constant Reynolds number of ,OOO,OGG. The results of the tes

12、ts indicate the following conclusions: 1. For all Mach numbers and Reynolds numbers in the test renge, no flow separation appeared to exist near the leading edge of the wing for lift coeffiaients less than 0.3. At higher lift coefficients the initiation of leading-edge flow separation with reattachm

13、ent, over the outer portions of the wing, was accompanied in nearly every case by an increase in the liftccurve slope, an increase in static longitudinal stability, and en increase in the.rate of drag rise. 2. The effect of increasing the Reynolds number at Mach numbers of 0.25 and 0.60 was to delay

14、 to higher lift aoeffioients the onset of flow separation near the leading edge and the concomitent effects on the Uft, drag, end pitching moment. , 3. Increasing the Mach number to approximately that for drag divergence at a Reynolds number of 4,OGO,OOO resulted in a rearward movement of the wing a

15、erodyneLoient of 0 to abbut 0.875 at a lift coefficient of 0.5.) Further increase in Mach number resulted in a rapid rearward movement of the aerodyxxt - z 90 95 loo Upper and Lcwer-Smfaces Ordinate 0 -804 0969 1.225 1.688 2-327 2.805 3 0199 3.813 4.272 4.6c% 4-837 4,968 4.995 4.894 4.684 4.388 4.02

16、1 3.597 3.127 2.623 2.103 1.582 1.062 .541 .02l i. E. radius, 0.687 . E. radius, 0.023 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM A51G31 e All. dbnmMcms in percent of chclrd UpperanaLower Sxrfacee station OraFnate 0 0 -63 .673 095 .8ll 1

17、.57 1.023 3.14 1.406 6.23 1.925 9.29 2.306 12.31 2.612 18.23 3.074 24.00 29.63 yg 35-13 40.49 ;:gg g-g 31788 55182 ?Z 60.69 3:2l2 65.46 2.910 70.12 2.574 74967 2.213 79-12 1.836 83.48 1.456 87.74 1.083 XE 1cm:oo :z ,014 I. E. radius, 0.485 F. E. radius, 0.016 19 Provided by IHSNot for ResaleNo repro

18、duction or networking permitted without license from IHS-,-,-20 IQEA RM A5lG31 TABIll III.- IXDEXOFTABULATEDPRECOEFFICS R X10- Table No, % rv 4.0 0.25 1% O“ tp 24O v VI VII VIII :g Ix X :E XI XII :g XIII -93 XIV -94 xv V :g XVII 02.5 xv311 2: .08 -25 xx $, 63 R, 4,m,QCJ. 4 M s, oa, lo, 2O, 3“. , uPP

19、ER5uRrAm Lm!m SmFAoLCt SePl- Angle of attmolc Angle or attack zr . Percent chord - o“ 1= 20 30 00 10 20 3= Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. 22 i I 2 i NA(?A RM A5LG31 TABLE IV.- CONTINUED. (a) =uI 0 , lo, PO, 3 - ConoluQeQ. F smi- ep

20、en utp. ?rrcent :horQ 10 20 0:0;6 -.023 .046 310 0:309 .I33 :08 .024 -.Ol -.oe 3 $39 f:o “7 7 :$76 -.031 $44 UPPER 8UFlFAcE Angle of attaok 00 16 20 3O 00 .o:o;g -ml09 -. 11 -.13 ? -.134 -.l 8 :k 3g -.144 I:;5 -:E 0.421 :g: -.115 1:1i5 -.1g z :2 -.150 -0153 33 -.I15 :o“Z+ ,040 0. 81 :$t I: -. 192 :

21、I: -.180 I:;% -.I.80 :i6t -.o 7 i -.o 2 .039 0.2Q 1:; :iig -.249 -.2 0 2 -.2 1 -.211 1: :;I -.19 z I: 53 -.os3 -.029 .03s 062 A;: fi g t c:f$ :1;1 :g -.lW -.171 :;g -.02 .Od 0.024 -. 692 -:tg -.per -. 23 31265 SE 3B :;g :FJg$ -033 0.707 b/2 e . 105 2.55 11:0 14.5 21.0 24.5 -:I% -.ll -.05 2 -.012 . o

22、hn 0.410 -.002 -. 1jg -.119 5085 -.w .004 .052 0.414 :f? 2 -.214 : IsI: -. 180 _i$g -.1t -.o 2 -.002 .046 O-g31 b/2 .052 zii -3s zyg zz H -. 197 -.187 -.I93 _:i7g -.105 -.a9 -.o 1 t .o 3 0.924 b/2 105 25 11.0 14.5 21.c f?c5 z IL:5 hk; 5l.C 754: 2 ;:2 or074 :$I?; -.062 -.lOl I: ;319 -.12 -.12 f -.123

23、 -.121 2 .004 .05s 0:17s .o 0 2 .o 1 -.o 7 Xx$ : :09“6 bu“7 -.ll f -.111 -.081 -3g 0:2,-, .lO .a3 J ,016 -.014 I:$; -.086 -.ogel 1: :o“g -.I05 I: 76 z .0043 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA FM MlG3 e TA6I.E Iv.- CONTINOEO. (b) sul

24、 4“. 60, go, loo. UPPER suRFMs LOYPR aT5rMc Semi- hglm or l tta0k 6 6O loo 23 . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-24 NACA F R, t,oOO,ooO. * (a) G, o”, IO, 200, 3O. 27 Provided by IHSNot for ResaleNo reproduction or networking permitted

25、without license from IHS-,-,-28 NACARMMX31 TABLE v.- CONTINUED. (a) %, O“, lo, 2, 3 - Conoluded. UPPER SURFME LONER SURFACE Seml- Pefaent krgls of attack hgle of l ttaok rpan Bta. ahord 00 10 20 3O 00 lo 20 3O 0 14.5 21.0 0.707 b/P 0.831 b/P 0.924 b/2 Provided by IHSNot for ResaleNo reproduction or

26、networking permitted without license from IHS-,-,-NACA RM A5lG31 29 TmLE V.- CONTINUED. (b) Q* kO, 60, a=. loo. UPPER SURFAOE wlml BOELFAOE Beni- &CLs of attaok Bpan eta. zrt Angle or sttaak 4O 60 so loo 40 60 sa LOO Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-