NASA NACA-RM-A54J20-1955 Effect of taper ratio on lift drag and pitching-moment characteristics of thin wings of aspect ratio 3 with 53 1 degrees sweepback of leading edge at subso.pdf

《NASA NACA-RM-A54J20-1955 Effect of taper ratio on lift drag and pitching-moment characteristics of thin wings of aspect ratio 3 with 53 1 degrees sweepback of leading edge at subso.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-RM-A54J20-1955 Effect of taper ratio on lift drag and pitching-moment characteristics of thin wings of aspect ratio 3 with 53 1 degrees sweepback of leading edge at subso.pdf（26页珍藏版）》请在麦多课文档分享上搜索。

1、Q wi - 1 _. . RESEARCH MEMORANDUM EFFECT OF TAPER RNXO ON LEFT, DRAG, AND PITCHING MOMENT CHARACTERSTICS OF TKCN WINGS OF ASPECT RATIO 3 WITH 53. lo SWEEPBACK OF LEADING EDGE AT SUBSONIC AND SUPERSONIC SPEEDS By Benton E. Wetzel NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS WASHINGTON January 27,1955

2、- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RMA5ti2G NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS RESEARCHMEMORANDUM EFFECT OFTAPERRATIO ONLD?T,DRA.G,ANDPITCHING- l43GXC CHARACTEBISTICS OF THIN WINGS OF ASPECT RATIO 3 WITH 53.1 SWEEPBACK OF

3、 LEADINGEDGEAT SUBSONIC AND SUPERSONIC SPEEDS By Benton E. Wetzel The results of a wind-tunnel investigation are presented which show the effect of the variation of taper ratio on the -lift, drag, and pitching-moment characteristics of tplin wings of aspect.ratio 3 with 53.1 sweepback of the leading

4、 edge. Three wings, tith taper ratios of 0, 0.2, and 0.4, in combination with a high-ftieness-ratio body were studied ti the investigation. Measurements of the forces and momenta on the wing-body combfna- tions were obtained throughout an angle-of-attack range from -4 to a maximum of +17O at Mach nu

5、mbers of 0.6 to 0.9 and 1.2 to 1.9. All models were tested at a Reynolds number of .3.0 tillion per foot at all Mach numbers. (This corresponds to Reynolds numbers varying from 2.9 to 3.6 million when baaed on the mean aerodynamic chords of the models.) In addition, the models were tested at Reynold

6、s numbers of 4.0 million per foot at all subsonic Mach numbers and 6.0 million per foot at Mach numbers of 0.8 and 0.9. Static longitudinal stability at subsonic speeds was reduced near a lift coefficient of 0.5 for the wings with taper ratios of 0.2 and 0.4. Variation of taper ratio did not affect

7、the minimum drag coeffi- cient at subsonic speeds. At supersonic speeds increasing the taper ratio resulted in a slight reduction in the minimum drag coefficient. Drag due to lift was decreased at all Mach numbers by an increase Fn taper ratio from 0 to 0.2. Provided by IHSNot for ResaleNo reproduct

8、ion or networking permitted without license from IHS-,-,-2 NACA RM A54520 INTRODUCTION Aa part of the continuing investigation of low-aspect-ratio tinge. by the NACA, the effect8 of taper ratio on the aerodynatic characterietice of Bwept wings of eJspeCt ratfo 3 at SUbBOniC and Bupersonic 8peedB hav

9、e - been investigated in the Ames 6- by 6-foot supersonic wind tunnel. This report IB devoted to the presentation and discussion of the results obtained during thi8 Btudy. b E C CD CL cm 4 D M Q R S Y a h NOTATION the effects of separated flow were shown to increase with increasing taper ratfo. The

10、static longitudinal stability at sub- sonic speeds was reduced near a 1Lft coefficient of 0.5 for the wings with taper ratios of 0.2 and 0.4. Although the most satisfactory varia- tion of pitching-moment coefficient with lift coefficient was obtained for the triangular wing, used to investigate a ta

11、per ratio of 0, the degree of instability for the wing with taper ratio of 0.2 was much less severe than that for the wing with taper ratio of 0.4. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-8 NACA RM A54520 Variation of taper ratio did not affe

12、ct the minimum drag coeffl- cient at subsonic speeds, while at supersonic speeds an increase in taper ratio resulted in a slight reduction in the minFzrmm drag coeffi- cient. Drag due to lift was decreased at all Mach numbers by an increase in taper ratio from 0 to 0.2. Ames Aeronautical Laboratory

13、National Advisory Committee for Aeroxxxtics Moffett Field, Calif., Oct. 20, 1954. a w- - REFERENCES 1. Frick, Charles W., and Olson, Robert N.: Flow Studies in the Asymmetric Adjustable Nozzle of the Ames 6- by 6-Foot Supersonic Wind Tunnel. NACA RM AgE24, 1949. 2. Anderson, Adrien E.: Chordwise and

14、 Spanwise Loadings Measured at low Speed on Large Triangular Wings. NACA RM AgB17, 1949. m 3. Lange, ROY H., Whittle, Edward F., Jr., and Fink, Marvin P.: Investi- gation at Iarge Scale of the Pressure Distribution and Flow Phenomena over a Wing with the Leading Edge Swept Bach 47.5 Having Circular-

15、 v Arc Airfoil Sections and Fquipped with Dropped-Nose and Plain Flaps. -. NACA RM LgG15, 1949. 4. Mitchell, Jesse L.: The Static and Dynamic Longitudinal Stability Characteristics of Some Supersonic Aircraft Configurations. NACA RM L52AlOa, 1952. - 5. King, Thomas J., and Pasteur, Thomas B., Jr.: W

16、ind-Tunnel Investiga- tion of the Aerodynamic Characteristics in Pitch of Wing-Fuselage Combinations at High Subsonic Speeds, Taper-Ratio Series. NACA RM L53E20, 1953. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NacA m A5kr20 9 TABLE I.- AEtRODYX

17、AMICCEARACTERISTICSOFTRIAmGuIARWLNG (a) R = 3.0 million per foot 16 a CL J.60 0.70 Og .a7 .024 .a31 -:z -.oog -.oll -.op :g 1:s -*Cdl :g -A36 -003 a06 .OlO .i$ zz :g -.032 :z -069 “Jg -.gP -.037 -.oiQ -A41 -.2X -:S :Z :g :g .!M +20 :g$ :z -:Z .o*g :15 .46 l. 8“:g 10.58 l2.73 14.93 17.04 lt3.W -A -55

18、 -1.m -2.36 -3.38 -4.47 -03 :; 2.03 :g 6.32 8.50 lO.Gb g:“, 17.12 la.17 0.032 .2 -023 -033 .m -.Wl -.004 -.OlS -.G!O :z -.og4 :gg r :z -.057 2% .m8 .015 :ZgZ -001 0 -.Ol -.a2 -.ml -.032 :g :z -.06c -as8 -069 .003 :g -017 :E .ool -.KJl -.oo: -.olk -.aa :g -.osc -.a 0.80 0.90 1.23 1.30 1.50 12.89 15.0

19、1 17.lO l8.L8 11% -1.23 -2.33 -3.45 -4.36 -03 1% 1.99 Z:E 2: 0.795 g -.032 :g :z :g :g J-32 .2l4 :g A04 -.a29 -.044 -:% -.ug -.291 0 .02L -055 .lzl .I92 .z -.026 -AC -.m :g -.2G .ca2 .org :ZE :Z :2$ :E -.022 -.c :% -690 -.OlT -.cfas -.Ogo I:% -.L78 .002 .Ol4 :% :g 248 :Eg -479 22 .65l 3.032 :Z 3 -.o

20、A -.0X2 :Z :gg -.ll2 -.137 -.159 -.173 -.I% .og .oQs :Z :% a -.003 :g -.op -.; AERODYNAMIC CHARACTERISTICS CZF WING WITH TAPER RATIO OF 0;2 - Concluded (b) R = 4;O million per foot an 0.003 :3 .ol4 .022 .03l 0 -.Wl -.Cdl -.Oll -.olg :F$ I:$ -.054 :g -a3 .a03 .W5 M a H a c, 0.d :z -035 .Wl -.Wl :Z -.

21、cQl -.031 -.04g -.oz :gg -.w .0g a -A0 -. -1.25 -2.38 -3.50 -4.64 :Z 2:g 3.16 kg3 I- .0065,: .oOn .OlOO -.014 .0147 -*Cdl :Eg -.035 1iig :z :gg 1.60 I.70 -r):g -1.P -2.30 2-z :GZ 1% 1.96 E 6.33 8.53 g.g 15:10 ;.$ . 1:; -0.030 -.045 -.076 -.136 :Z -.a16 -016 At8 .llO 1% .38-l 2: :g 1% :“A I.0073 :Zi

22、.Oll3 :%2 :Z$ .oo75 :E2 :tZ -0775 .1171 .1689 .z .Qm .0075 1.7C -1.23 -2.32 -3.44 .4.55 g 1.98 Ei :2 lo.79 g:zT 2 -2.34 “:E :g -.006 .016 :Fg .I81 E 22 $2 -.03r :$ -.=3 -.w -*cm3 ).0087 .au5 22 :Z .cm4 .olol .0141 :$E :ES .17* 2280 .0068 :zE .0182 :Z: .z 22 .0123 :Z .mgo .035 .a011 .w .w61 .(xIl 1.8

23、0 SW62 -.W2 :E 11% .WJ+ -.03l :$E -.a55 -CCL (c) R = 6.0 mil.Uon per foot 1.0076 .Oo78 .oos7 m.35 .OlS .0263 ;z .Olcxl .oPJ8 .02lU :% c, c, M a CD ).00?5 :g .OIp .ol87 .03cm ZJ :2 :$ CL -0.036 -.cfJl :$ -226 -.zslr -.wl .m5 :Fig .1g1 .a63 .4l8 .533 MC -0.W -.72 -1.29 -2.42 -3.59 -4.74 ;Tj 2.07 Z:$ 0

24、.003 2% :Z .035 0 -.w3 :% -.a3 -.0p -.052 -.060 0.035 -.m :z -.244 -.331 -.002 :Z .lP .z “23 :% :E 0 :gg -.017 -.op :z: t C Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM A5020 13 TABI III.- AERODYNAMIC CEARACJXRISTICS OF WIXG WITI TAPER RAT

25、IO OF 0.4 (a) R = 3.0 million per foot H Ig :ZZ -.org -.033 -.059 cn c, 3-17Lg -xc .=7 -2735 -.03-i .3KQ -038 .oqo 0 .oOl :z .cm5 .m5 .OlO :Eg :E$ -*cm -.Wl -.005 :Z -.Ol2 -.02l .a32 -.037 .ow -OS7 .og21 -a78 .oose 1% .0105 :%2 -014 .ml .OlB . 2% -373 :;g .614 $2 -.ol8 -.=9 -.052 -.osa -.lJ!a -.l83

26、-003 .a4 :Z :g :g :ig 2% .9 j-0153 .m3 -4 - Concluded (b) R = 4.0 million pe-r foot . a cc cr. -0.39 -A8 -1.24 -2.25 =; :0-l .36 .92 2.01 Z:“, t:g 10.83 13.01 15.19 .O.On -.039 -.o6g -.13l -.lg6 -.ti7 .005 :Z .115 :Z AQO 2% .7b -858 -.42 -.022 -.4 -.Oj6 w cr. cDle I Loce4 0.001 .oll.4 .ti .Ol% .0231

27、 12 .0069 -.OOl -0074 -.OOl .m32 -.cKQ .010-r -.octi .OW. -.OlO .02lg -.ol5 ;yg -.O% :i$ :2% -.032 -.Qa .2793 -.017 .31ol -.a3 .a59 .012 .g .175 .2d -394 .533 .a5 :g; .9+5 .9-B -.m6 -277 ).cK% -0.001 .0070 -.wl .i;crlB -.003 .Oloa -.W3 .W -.ol3 .a?28 .g ! :$ .01g -.Wl 23: -.W2 -.003 .OlW -.00-f .olg

28、z -.o.l.l tz -.017 -.o$l -.Ogl a CL I Q 1% . -0.47 -.77 -1.34 -2.44 I:-$ :07 :z 32:Z 4.46 6.78 -0.030 o.c178 o :g .0079 .001 .OW .m3 -.lp4 .om .oog -.23l .0182 .a27 -.3ll -0277 .030 .olo :E2$ -.ti -.W :g .oo% -.005 23 .OlO8 .0157 22 :z :$ -.028 -.osl I I v Provided by IHSNot for ResaleNo reproductio

29、n or networking permitted without license from IHS-,-,-Figure I.- Model tith wing of taper ratio of 0.2 installed in Ames 6- by 6-foot supersonic wfnd tunnel. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-r ( ! + I- 4693-4 (a) Taper rotion0. - (c)

30、Toper ratio q 0.4. 4693-4 (b) Taper rotio=0.2. Moximum radius, r,= 2.38 Length for closure, I = 59.50 All dimensions In inches unless atharwiss noted Figure 2.- Dimensionsl sketches of modela. , I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.6 -4

31、 0 4 6 12 16 20 (for M-.6) a, de3 Figure 3.- Hfect of taper ratio on the variation of lift coefficient with angle of attack; R L 3.0 TI.CUUO per foot. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-101 t w Mu I I I I I I I I I IoX= 01 I .8 I I I I I

32、 bX=O.41 I I I I I I I I I I I I .6 :54 0 704 -;08 (for hl=.6) Cm Figure 4.- 52 Bfect of taper ratio on the variation of pitching-moment coefficient with lift coefficient; R = 3.0 millIon per foot. 54 ii 1 , C 1 I I ! I Provided by IHSNot for ResaleNo reproduction or networking permitted without lic

33、ense from IHS-,-,-, L 1.0 .8 .6 .4 “. 2 3. 4 - - - - - - - - - - .04 a08 .I2 .I6 .20 .24 .28 -32 (for M =,6) CD Figure 5.- EkPfect of taper ratio on the variation of drag coefficient with lift coefficient; R = 3.0 million per foot. Provided by IHSNot for ResaleNo reproduction or networking permitted

34、 without license from IHS-,-,-20 .x NACA m 5U20 20 I - k= R = 3.0 million per foot. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I I L , I , IO 8 6 4 2 0 0 .2 .4 .6 .8 1.0 (for M=.6) CL Figure 7.- ETfect of taper ratio on the variation of lift-dra

35、g ratio with lift coefficient; R = 3.0 million per foot. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- I.U 0 Rm3.010 per ft I I I I I I L-l-4 I AFI I d ac I I n R-4.0x10 perft / I IOR-BOxId wr ft I I I I I I I I I I t I Id d 0 4 6 x)4 0 -.04 -.06

36、-.I2 Weg cm (a) h = 0 Figure a.- EPfect of Reynolds number on aercdpau!lc characteristics of the three mrdel.8 at a hbh number of 0.8. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I L 0 .04 .08 -4 0 4 8 .04 0 -.04 -.08 -.I2 CD Vw Gl (b) h = 0.2 j.

37、gure 8.- ContJxtued. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.6 0 4 W-v (c) h = 0.4 !$ 8 .04 0 -.04 -.08 :g Clll E Figure 8.- Concluded. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-E 25 c ” .08 .06 CD .04 .02 0 0 .08 .06 CD .04 -3 -A coefffcients for the three models at subsonIc spee&. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-