NASA NACA-TN-3501-1955 The transonic characteristics of 22 rectangular symmetrical wing models of varying aspect ratio and thickness《有不同展弦比和厚度的22矩形对称机翼的跨音速特性》.pdf

《NASA NACA-TN-3501-1955 The transonic characteristics of 22 rectangular symmetrical wing models of varying aspect ratio and thickness《有不同展弦比和厚度的22矩形对称机翼的跨音速特性》.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-TN-3501-1955 The transonic characteristics of 22 rectangular symmetrical wing models of varying aspect ratio and thickness《有不同展弦比和厚度的22矩形对称机翼的跨音速特性》.pdf（110页珍藏版）》请在麦多课文档分享上搜索。

1、(xi_(FORAERONAUTICSTECHNICAL NOTE 3501THE TRA3WONICCHARACTERISTICSOF 22RECTANGULAR,SYMMETRICALWINGMODELSOF VARYINGASPECT RATIO AND THICKNESSBy Warren H. NelsonandJohnB. McDevittAmes AeronauticalLaboratoryMoffett Field, Calif.WashingtonJune1955.1-Provided by IHSNot for ResaleNo reproduction or networ

2、king permitted without license from IHS-,-,-TECHLIBRARYKAFB,NM1A NATIONALADVISORYCOMMTTEEFORAERONALJTICSlllllnllll!ullflllllnlnlUOLLL17TECHNICALNOTE3501THETRANSONICCHARACKDZRISTICSOF22RECTANGULAR,SBW121RICALWINGMODELSOFVARYINGASPECTRATIOByWarrenH.NelsonandTHICKNESSJohnB.McDevittSUMMARYAninvestigatio

3、ntodeterminetheaerodynamiccharacteristicsofa seriesofthin,rectangularwingswasconductedintheAmes16-foothigh-speedwindtumnel,utilizingthetrsnsonic-bumptechniqueoveraMachnumberrangefrom0.40to1.10,correspondingtoaReynoldsnumberrangefrom1.25to2.05million.Thelift,drag,md pitching-momentdatame presentedfor

4、wingshavingaspectratiosof6, 4, 3, 2,1.5, 1, and0.5, andNACA63AOmsectionswiththickness-to-chordratiosof10,8, 6, 4, and2percent.INTRODUCTIONThepurposeofthisinvestigationwastoprovidecomprehensivedataontheeffectsofaspectratiosndthicknessoncharacteristicsofa familyofsymmetrical,straightthetransonicspeedr

5、ange.Twenty-twowingsinallwereinvestigated,with6, 4, 3, 2, 1.5, 1, and0.5. Rectangularplanformsthecorrectionsfortheseeffectshavenotbeenmade.Theseeffectswouldbegreatestontheloweraspect-ratiowingssincetheyhavethesmallerarea.Themodelsinvestigatedonthetransonicbumpme mountedin”alocal,high-velocityregion.

6、TypicalcontoursoflocalMachnumberinthebumpflowfieldareshuwninfigure6. OutlinesoftherectangularwingshavebeensuperimposedonthesediagramstoindicatetheMachnmberadientswhichexistedacrossthewingsduringthetests.Noattempthasbeenmadetoevaluatetheeffectsofthesegradients.ThetestMachnumberspresentedinthisreporta

7、retheaverageMachnmbersoverthewings.RESULTS.Thedragdatapresentedhereinshouldbeusedwithcaution,particu-larlythat-forthelowerMachnumbersoraspectratioswherethemeasuredloadsweresmallcomparedtothecapacityofthebalance.Forthisreason, Provided by IHSNot for ResaleNo reproduction or networking permitted witho

8、ut license from IHS-,-,-NACATN3501 5.onlydataabove0.70Machnumberhavebeenusedinthecrossplotsinvolv-ingdragmeasurements.Otherfactorswhichcontributetotheuncertaintyofthedragdataarethelarge Jfor #of 0.40 .60 .70 ,7.s .80, .85 .9;(0.) G. vs a.Figure Z- Comparison of the aerodynamic choracterktics of the

9、tuptve aspect- rotlo- NAGA65,-2/0 wings, os obtained with o sting-mounted model and a bump-mounted model.IIProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Lo.80.2I.0 .0/? .04 .06 .08 .10 ,/k? ,/4 .16 .18 a20Drag due to lift, ACDIjjjAGOof 444forMof 0.

10、40 .;0 .)0 .7L .80 .85 .90(b) Drbu due to fft, Ac vs 6.Figure 7.- Continued.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-II/. o.80.Q Bump, semisp onn Sting, full spon./ o ?/Pitching-moment coeff/cienf, Cm(C) G V8 CL.Figure Z- Gonclucfe d,GProvided

11、 by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-P(n1.0.8.6Q“*.$,4$.$,250-.2-.4.74 O 4 8 12 16 20Angle of ottock, a, degUof+ + +J+forhf of 0.40 .60 .70 .75 .80 .85 ,90 ,94 ,98 1.02 /06 1.08(a) A, 6; i/C,0./0.Figure 8.- The varbtion of lift coefficient with an

12、gle of attach for the rectffngu/ar wings withIVA CA 63AOXX sections.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1I,I1.0.8-,2-.4+ O 4 8 /2 /6 20Angle of atack, u, degof+ $+; +44 +?+for M of 0.40 .60 .70 .80 .85 .90 94 .98 102 106 L08I(b) A, 6; f/C

13、,0.08.Figure 8.- Continued,sProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ral1.0.8-.2.7 4 O 4 8 12 16 20Angle ofotfack u,degaof+ + + + + + + + 4 4for IWof 0.40 .60 .70 .75 .80 .85 .90 .94 .98 102 1.06(c) A,6; f/c, o.06.Figure 8.- Confinued,Provided

14、 by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Lo.8.6b“$-.4* .2$0.2.4-4 0 4 8 /2 /6 20Angle of attact, a, degaof+b+b+?+for M of 0.40 .60 .70 .75 .80 .85 30 .94 ,98 102 106 I!8(d) A, 4 t/C, 0.10.Figure L!?.- ContinuedProvided by IHSNot for ResaleNo reproduct

15、ion or networking permitted without license from IHS-,-,-K)o10.8.J,6Cla-* .4*$g .2$o.2.44 0 4 8 12 16 2Angle of attack, a, deg(e) A, 4; f/c, i208.Figure 8.- Continued.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I,I1IL2/. o.8-.2-.4! I d I d IQ4 O

16、4 8 1P /6 20Angle of attack, a, degaof+bb+fw M of 0.40 .60 .70 .75 .80 .85 90 .94 98 102 L06 1081I,I(f) A, 4j f/c, 0.06.Figure 8.- ConthwxiI-owProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-auf+ + +forM of 0.40 .60 .70 .75 .80 85 .90 .94 .98 /02 106

17、 L08 1.10(g) A,4, i/c, Q04.Figure 8.- ContinuedrProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-III. .-4 0 4 8 12 /6 20Angle of aftock, a, deg.ofc)+i44i444for M of Q60 ,70 .75 .80 .83 .80 94 .98 /. 106 LOB(h) A, 3, f/c, c204.Figure 8.- ContinuedIProv

18、ided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-10-F1.0.8-.2-aII., 4 O 4 8 f2 f6 20Angle of ottock a, deg(i) A,2; f/c, O.10.Figure 8.- Continued.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I/.0.8.6u-.

19、2-.44 O 4 8 12 /6 20Angle of attach u, degaof+ +for M of 040 .60 .70 .75 .80 .85 90 .94 .98 I!02 /06 08 /.10(/) A, 2 t/C,0.08.Figure 8.- ContinuedProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-J2,8.6d.4 0 4 8 /2 16 20Angle of attock, a, dog“0+ 4+444

20、4 + 44444forkfof 0.40 .60 .70 .75 .80 .85 30 .94 .98 i02 L06 L08 I.10(k) A, 2; t/C,0.06,Figure 8.- ContinuedrProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-“74 O 4 8 12 /6 20Angle of attack, q degaof+f+(+l+q+ r+for M of 0.40 .60 .70 .75 .80 .85 .90

21、.94 .98 L02 L06 08 1.10(/) A, 2; f/c, Q04.Figure 8- ContinuedtProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1,0.8-.2-.4-4 0 4 8 /2 16 zoAngle of ottack, a, degff”f+b+h+ + Q+ $+for M of 0.40 .60 .70 ,75 .80 .85 .90 .94 .98 1.02 L06 08 1.10(d A, 2, f

22、/C,0,02.Figure 8.- Gonflnued.,Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.8.2-4“4 O 4 8 12 16 20Angle of ottack, u, deg.offl+l+l+for hi of 0.60 10 .75 .80 .85 .90 .94 98 /.02 /06 L08 110(n) A,l f/c, 004.Figure 8- ContinuedProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-