NASA NACA-RM-A50K20-1951 Lift drag and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds - plane triangular wing of aspect ratio 2 with NACA 0008-63 secti.pdf

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1、I , COPY 5 + -. 1-e RM A!XK20 RESEARCH MEMORANDUM LIFT, DRAG, AND PITCHIU MOMENT OF LOW-ASPECT-RATIO WINGS AT SUBSONIC AND SUPERSONIC SPEEDS - PLANE TRIANGULAR WING OF ASPECT RATIO 2 WITH NACA 0008-63 SECTION By Donald W. Smith and John C. Heitmeyer NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS i - T

2、- - 1 WASH,NGT*N ,. - f : i g-_*-r February 1, 1951 k -y.: i -;.- -i v- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1 . - - NACARMA50gX) -_-_ - ._ _ IUU!IOEALADVISORYCOMMI!ETlEFORARRCNC!3 RESEARCH MEMORANDUM ,DRAG,P;WDPTrCOF-IO AT suB3oNIc AND Su

3、PEmCN1csPRRD2 - PUIKEi TRIANGUUR WIKGOF ASPRCT.RATIO2WITRNACA OOOh53 EECTION By Donald W. Smith and John C!. Eeitmeyer suMMARY Axink-bodycinstionhavlngaplanetriKLngof aspect ratio 2 and NACA 0008-63 sections in streemise planes has been invee- tigated at both stZbs fig. 2) . , . . 12.5 Cross+ection

4、shape . . . . . . . . . . . . . . . . Circular Msximum cross-sectional area, square feet . . . . . . 0.204 Ratio of maximum cross-sectional area to wingarea.O.O509 The wing was constructed by covering a steel spar with a tHismuth alloy. The body spar was also steel but was covered with aluminum. The

5、 surfaces of the wing and body were polished smooth. Range of Test Variables The characteristics of the model (as a function of angle of attack) were investigated for a range of Mach numbers Pram 0.24 to 0.95 in the Ames U-foot pressure wind tunnel and fronn 1.30 to 1.70 in the Amea 6- by 6-foot sup

6、ersonic wind tunnel. Thelnajorportionofthedatawae obtained at a Reynolds ntDnber of 3.0 million. Data were also obtained for Reynolds nmbers up to 15.0 mUlion at low subsonic Mach numbers and up to 6.0 million at supersonic Mach numbers. Reduction of Data The test data have been reduced to standard

7、RACA coefficient form. Factors which could affect the accuracy of these results and the correD- tions applied are discussed in the following paragraphs. Tunnel*11 interference.- Corrections to the subsonfc results for the induced effects of the tunnel walls resulting from lift on the model were made

8、 according to the methods of reference 4. The numerical value of these corrections (which were added to the uncorrected data was: vs 7 0 .2 .4 .6 -8. I.0 1.2 br RI=.24 L/f? coeff/cM c; /d) GO ve C,. Figure 3.- Concluded. Provided by IHSNot for ResaleNo reproduction or networking permitted without li

9、cense from IHS-,-,-I I I I I I A R= 3.OmHkn 0 R=15.0mNn .04 .08 ./2 .I6 20 .24 .28 .32 .36 .04 0 :04 08 :I2 -J6 Drag coefficient, Co titchihg-moment coefficient Cm -4 0 4 8 I2 16 20 24 Angle of attack, a, deg v fo) M1.24. Ftre 4. - The variatbn of the ae#wmk cbofactefieke wifh lift coefEkieni at var

10、/ous Reynolds numbers. . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 , I . et3 , t .8 h#a 0008-8.3 -nhp n/ P /I /I d A bi Id r I drl I I I I I I K I I I I I I Y -2 I I I I I I I I AR = 3.0 millron -A I I I I I I I I II.1 I I W?= 5.0 million r

11、7 0 .04 .08 ./2 .I6 020 .24 .28 .32 .36 .04 0 04 708 112 -.I6 Drag coefficient, CD Pirching-moment coefricitwt, Cm -4 0 4 8 f2 16 20 24. Angle of attack,. ,a, deg -Yjjz28 04 0 04 08 ;2- / -.I6 -.20 Drag coefficienf, Go - Pitching -moment coefficient, Cm -4 0 4 8 /2 I6 20 24 WV Angle of attack, 0, de

12、g (d) M * 1.70, Figure 4, - Concluded, Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-20 NACA RM A!XIS20 -: Resuffs from Ames 6x 6lt! 7: 0 0 2 .4 .6 .8 I.0 f.2 I.4 I.6 LB Moth number, M -.2 Y / -Resu/fs from Ames /ZH! 7: -t?esdfs from 0 Ames 6x 6W:

13、7: 0 2 .4 .6 .8 l.0 I.2 f.4 66 /.8 Mach number, M Ffgure 5. - Scunmary of awoojmomic chwocferisffcs as u funcfion of Much num&er. ffeynokfs number, 3,Omi/on. I - -. . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-WACA RM A5OK20 21 . 161 1 1 1 If 11

14、 11 II t t t 1 I I I t I I I I I I -Resu/fs from Ames 6xt?U! T f 1 i i i - 0 .2 -4 .6 .8 I.0 i.2 1.4 1.6 l-8 hfuch number, M . 9 ./ t I 1 I I I I I I 0” Results from Ames /2W. iT - Resu/fs from Ames 6x6W.b 0 0 .2 -4 .6 .8 LO I.2 /.4 i.6 I.8 Much number, M FiQwe 5. - Confhued. Provided by IHSNot for

15、ResaleNo reproduction or networking permitted without license from IHS-,-,-22 lM!A FM AK20 20 .i8 ./b .04 t i I A i i i i I i i i i I / * i I I i i i i i i i i i 0 0 .L .4 .6 .8 I.0 I.2 I.4 i.6 i-8 . Much number, tW fel Co vs M. - 4 ._.- 1 w- Figure 5.- Conchfed NhCh-Uncg -t-l-61 -646 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1 . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-