1、/ -.-. , ,-. .NATIONAL.,ADVISORY COMMITTEEFOR AERONAUTICSTECHNICAL NOTENo. 1422* EC 1947EXPERIMENTAL AND CALCULATED CHARACTERISTICS THREE WINGfOF NACA 64-210 AND 65-210 AIRFOIL SECTIONSWITH AND WITHOUT 2 WASHOUTBy James C. SivellsLangley Memorial Aeronautical LaboratoryLangley Held, Va.FORREFERENCEW
2、ashingtonAugust 1947 IJENARYcop.I ;.+30 m IlAiiiLIBRARYNASAHAMPTON,VIRGINIA, : ,“ ,”;: .:, .,!:., .“.;., .”: .“” ”:”, $.” ,:” . . .:;”) :$, . . .a71 ,1,:.;.,:;EXPERi3lWALh) CALOUIhD CHUWTERISTWS (IFTliii:iiiiiiGBm:“”k:“:,:#-, ,“OFNM!A.6 : .:. ., . . .:.,.,”, ,. .“. .An invest. .;.“,effectsofairfoils
3、ectionandWashdtiton Weexperimental,.k changingtheairfoilsectionfromm NW 61XZL0 S?ctfOnto ,NACA64-21o section was to increase theznaxiqm Mft “coefficientby .about1.0percent,althoughtheabruptnessofD“liftcoefficientmaximumvalueofdragcoefficient(D/)profile-dragcosfficient(Do/) minimumvalueofprofile-drag
4、coefficient.pitohiqpmaentcoefficient(M/6)Glift . .drag%Lb.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3UCA NO, 1422: 3(L/D)- vaheof ratioofliftto draghagIncwnmlprofilejtchingmomentabout0.256namicpressureoffreOstreem(9) six-ccauponent baknce qyste
5、m. The profiledr was determined from the force test data and also by thawake-momentunmethodfrcmsurvuysoftheairflowinthewakeofthewingat 19 spenwise stathns. Thestallingcharacteristicweredeterminedframobervationsofthebehavioroftuftsattachedtotheuppersurfaceofthewln hehlndthe0.30chordU.ne. .RESUUJ!SAND
6、DISCUSSIONAlldatahavebeenreducedtostandardnondimensionalcoefficiarcts.CorrectionshavebeenappliedtotheforceandmomentdatatoaocountforthetareamdinterferenceeffectsoftheuthepointoftangencyofthetwocurvesindicatesthesymrisepositionofWe initialstall,andtherateofdivergencebetweenthectc?vesservesasanindicati
7、onofthemannerInwhichthestallseads.Frornaccmqyxrisonoffigwes 5 and6,itcanbe seenthatthesewingsstallapproximatelyaspredicted,.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-6, ,. Eifecrt of Airfoil Swtbn,A comparisonofftguree2 and 3 showsthat the mini
8、munI pzktile -drag mefficien of the NAOA64-21o WIW iS d.IItlyhier (about C)a71000k) tha that of the I?MA65-22.0wing and thomaximum.lii%-larger.mount ofwahoutshouldetfecta signlficantimprovmmntbymovingthestallfarther iritxmrd., .:(101V2LUSiOILSFromtherS.lW.CARep.llc.572,1936.,Characteristics of“#a71.
9、,.b.k.TProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-“1(L/D)=lllE%yu =(IQ) -CalsumtdWJ.oataa Oalclaataa1.361.35.1.21.1.230.0%”.085.0850.083 -1.0 -1.1“1.0-1.538.839J+ .38.038.841.041.6.1.24 .0e5 -1.0a71o ratio of root chord to tip chord, 2.5. (All d
10、imensions are in inches. )a71g.* -:, .! tProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-a71 aspect ratio, 9; ratio of root chord to tip chord, 2.5; R % 4.4 x 106 ; M x 0.17. .Provided by IHSNot for ResaleNo reproduction or networking permitted witho
11、ut license from IHS-,-,-,. ,.,./.2/.0.8.6cl.4.20- Csleulatad-+I 1%1Ii -o Inm2etams 140 .004 008 .0/2 0.02 #DfS,.iO-4 048/20 7/co CDo # cm.Figuxe 3.- Experimental and calculated characteristics of wing having NACA 65-210 airfoil sections.Washout, 2; aspect ratio, 9; ratio of root chord to tip chord,
12、2.5; R x 4.4 x 106; M z 0.17.* -, .-. lm, -, ,Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-#m -.;*/.4/.2/.0.8.6q.4.20, , , # 1 1 “ 1/ o tI I I#i a II1 -O Fbrcet4A0 Do4a08t22 0 .02040608./0-4 048/20 7/CDO c u- c8Figure 4.- Experiment aspect ratio,
13、9; ratio of root chord to tip chord, 2.5; R % 4.4 x 106; M z 0.17.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-,.RoughflowInfermiffd stillMCotnplde doll-nd/Cressflowa:t3. o” +-1.18 a. 0017m.(cJ NAC$Y%J;( WM79;.of root chord to tipchord 2.5.2ga.Pro
14、vided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-/.6M2C*0.8.6cz=i1 1NATIONAL ADVISORY COMMITTEE FORAERONAUTICSb ,(b) NACA65-210 sections, 2washout.Figure 6.- Continued.*4 w a71 *Y. . . . .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. .,*+* a71a15r -x w 4.4”L6L4L2Cz10.8.6.4cz=COMMITTEE FORAERONAUTICSo ./ .2(c). 5 .6 .7zy/bNACA 65-210 sections, 0 washout. 8 .9Figure 6.- Concluded.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
