NASA NACA-TN-3007-1953 Lift and pitching moment at low speeds of the naca 64A010 airfoil section equipped with various combinations of a leading-edge slat leading-edge flap split f.pdf

1、-TECHNICAL NOTE 3007LIFT AND PITCHING MOMENT AT LOW SPEEDS OF THE NACA 64AO1OAIRFOIL SECTION EQUIPPED WITH VARIOUS COMBINATIONSOF A LEADING-EDGE SLAT, LEADING-EDGE FLAP,SPLIT FLAP, AND DOUBLE-SLOTTED FLAPBy John A. Kelly and Nora-Lee F. HayterAmes AeronauticalMoffett Field,Labol atoryCalif.Washingto

2、nSeptember 1953. _ -Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-IECH LIuRAnV kAt6,NMlW.-,I!lllllll!lllnllllulluNATIONAL ADVISORY COMMITTEE FOR AERONAUT!00LLJ?Lmmmlm NOTE3007LIFT AND PITCHING MOMENT AT LOW SPEEDS OF THE NACA 64AO1OAIRFOIZ SECTION

3、EQT.IITPEDWITE VARIOUS COMBINATIONSOF A LEADING-EDGE SIAT, LEADING-EDGE FIAP,SPLIT IT therefore, the span wasshortened approximately 5 inches by the installation of liners on thetunnel floor and ceiling. The liners extended approximately 4.5 feetupstream of the leading edge and 3.5 feet downstream o

4、f the trailing edgeof the basic airfoil model.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 Iwx TN 3007In the present investigationthree model arrangements conformedgeometrically to the basic airfoil (ref. 1): the model with the leading.edge flap

5、 (bn = 0) and no trailing-edge flap,l the model with the slatretracted and no trailing-edge fla-p,=and the model with the shit retrac-ted and the double-slotted flap retracted. Coordinates for the basicairfoil and for the different components of the model.are presented intable I. FiWe 1 shows sectio

6、ns through the various hi-lift devices.The model installed in the wind tunnel is shown by photographs in fig-ure 2. The 600 deflection angle for the split flap and .7 for thedouble-slotted flap were selectedbecause these values are believed tobe about optimum for the ratios of flap chord to airfoil

7、chord thatwere used.Measurements of lift and pitching moment were made with the wind-tunnel balance system. For the most part, the tests were conducted at aReynolds number of 6 million. Data also were taken for Reynolds num-bers of 2, 4, and 7 million for the basic airfoil model, the model withoptim

8、um slat settings, and the model with leading-edge-flapdeflectionsof 10, 20, 30, and “. The folloying table summarizes the condi-tions for all the tests:Rx 10-6 -c pressure, Machlb/sq ft number2 5 0.0620 .122 40 h .17I 7 I 60 I .20 IThe data have been corrected for the influence of the tunnel boun-da

9、ries with the use of the appropriate relations given in reference 2.To assist in the determination of stallingvations were made of the flow over the model asby the chordwise distribution of pressure.Lift andgeometricallyRESULTS AND DISCUSSIONBasic Airfoilcharacteristics,obser-indicatedby tufts andpi

10、tchtng-moment curves for the three models correspondingto the basic airfoil are presented in figures 3 and l(a)(F)n = 0“)= The purpose of the following discussion is to point out thechanges in cl- that resulted from replacfng the leading-edge flapwith the slat and from alteration of the trailing-edg

11、eregion tot.,lBefore adaptation for the double-slotted flap.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN 3007 5.accommodate the double-slotted flap. The data from figure 3(b)(R = 6 x 108) and figure J(a) (bn = 0) show that ck was 0.90 fort

12、he model with the slat retracted and no trailing-edge flap and 1.10for the model with the leading-edge flap unreflected and no trailing-edge flap. The possible effects of leakage around the slat were inves-tigated by sealing the upper and lower surface slat-wing junctures. Acomparison of the results

13、 for the model in the sealed and unsealed con-ditions showed no changes in the lift or pitching moment. The effect ofrevising the trailing-edge region to permit the installationof thedouble-slottedflap was to increase cl- from O.90 to 1.03 (fig. 3(b),R= 6X106). Similar increaseswere obtained for the

14、 other values ofReynolds number. Data for the model with the leading-edge flap (bn = 0)and no trailing-edge flap will be considered as the basic airfoil datafor this report since they correspondmost nearly to the data from refer-ence 1. With either type of trailing-edge flap deflected there was litt

15、leor no difference in the value of Czma for the model with the slatretracted or with the leading-edge flap unreflected.Leading-Edge FlapThe data presented in figure 5 show the effect of varying the deflec-tion of the leading-edge flap on the maximum lift coefficient for themodel with different trail

16、ing-edge-flaparrangements. The maximum liftcoefficientwas increasedby increasing the leading-edge-flapdeflectionup to an angle which was dependent on the Reynolds number. For a Reynoldsnumber of 2 x 106, the curves reach their peak values for a deflectionangle of approximately 40. For the higher Rey

17、nolds numbers, the peakvalues were reached at approximately 30 deflection. The absence of datafor leading-edge-flapangles between 0 and 40 for the model with asplit flap at a Reynolds number of 7 x 106 is due to having stopped theseruns prior to attaining czu because of extremelyviolent shaking ofth

18、e model. The dashed curve was drawn through values obtained forbn = 0 and 40 and from increments of Ctma, produced by the trailing-edge flap, extrapolated to a Re”ynoldsnumber of 7 x 106.In figure 4 are shown the lift and pitching-moment characteristicsof the model for various deflections of the lea

19、ding-edge flap. Thelinear portion of the lift curve for the model with a trailing-edgeflap was decreased considerablyby increasingthe leading-edge-flapdeflectionbeyond 30.The stalling characteristicsof the various model arrangements asindicated from observations of tufts and pressure distributions a

20、re class-ified in accordancewith the types described in reference 3. The type ofstall associatedwith the plain NACA 64AO1O airfoil section- leading-edgestall (abrupt flow separation near the leading edge without subsequent-. - .Provided by IHSNot for ResaleNo reproduction or networking permitted wit

21、hout license from IHS-,-,-6 NACA TN 3007reattachment) was not altered by deflection of the leading-edge flapfor the model with no trailing-edge flap. However, the chord-wise loca-tion of the point of flow separationwhich was near the leading edge ofthe leading-edgeflap for deflectionsup to 150, move

22、d downstream of theleading-edge flap for deflections greater than 15. Deflection ofthe split flap for the model with 8n = 0 resulted in a change to thethin-airfoil type of stall (flow separationat the leading edge, priorto attaining c2_, with reattachment at a point which moves progres-sively rearwa

23、rd with increasingangle of attack), but leading-edge-flap deflections of 5 or greater caused the stall to revert to theleading-edge type. Deflection of the double-slottedflap resulted in atrailing-edge stall wherein the attainment of cz_ corresponded tothe flow separationhaving progressed forward to

24、 approximately the 60-percent-chord station,regardless of the amount of leading-edge-flapdeflection.Leading-Edge SlatDetermination of optimum slat positions.- The effect of slat posi-tion on the maximum section lift coefficient is shown by the contours infigures 6, 7, and 8. The highest values of th

25、e maximum section liftcoefficientare plotted against slat deflection in figure 9. The posi-tions correspondingto the peak values shown in figure 9 will be referredto hereinafter as optimum positions. Reference dimensions for thesevarious positions are given in the following table:slat in optimum %39

26、 Ys9 Gap, s)position for the percent percent percent degmodel with - chord chord chordNo trailing-edgeflap 9.2 -8.7 1.60 25.6split flapdeflected 600 8.2 -9.3 1.25 29.1Double-slottedflap deflected52.7 7.9 -8.1 1.10 26.1The changes in optimum slat position due to deflection of the split flapare consis

27、tentwith the trends noted in reference 4. Deflection of thetrailing-edgehigh-lift devices caused the optimumchanged in such a manner as to reduce the gap.In an attempt to obtain some criteria for theleading-edge slat to attain high values of maximumspending to the highest values of c2- from theslat

28、position to bepositioning of alift, data corre-contour plots ofProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN 37references 4 and 5 and from the present report were correlated. Iheresults are presented in figure 10. The graph of (Ax/X) as a f

29、unctionof gap/T indicates that, if the relation of Ax to the gap is adjus-ted for the geometry of the concave surface of the slat, there is but asingle value of Ax for a given gap whichwill produce the highestCZW for a particular slat deflection.The contour plots from the present report and referenc

30、e 4 were usedto check the reliabilityof the curves drawn in the graphs of -(Ay/ with the split flap deflected,2.81 (fig.U(b) );and with the double-slotted flap deflected, 3.10.025.020.025.030.035.040.045.0%60.065.070.075.080.085.090.095.0lm. oOrdinate0.804.9691.2251.6882.3272.8053.1993.8134.2724.606

31、4.8374.9684.9954.8944.6844.38434.cel3a71 5973.1272.6232.1031.5821.062.*1.021L.E. radius: 0.687T.E. radius: 0.023IowerStationoa715.751.252.5R10.015.020.025.030.035.040.045.0.o55.060.065.070.075.080.085.090.095.0100.0l-lLEADING-EDGE SLAT, ANDof airfoil chordurfaceOrd-mateo-.804-.969-1.225-1.688-2.327-

32、2.805-3.199-3.813-4.272-4.606-4.837-4.968-4.995-4.894-4.684-4.388-4.021-3a71 597-3.127-2.623-2.103-1.*-1.062-.*1-.021Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-12 NACAm 3007TABLE I.- COOKDINATES OF NACA 64AO1OOIL, LEADING-EDGE SIAT, ANDDOUBLE-SL

33、OTTED FLAP - Continued.Stationssnd ordinates given in percent of airfoil chord .Slat lower surface Upper surface ofairfoilStation Ordinate Station Ordinate4.7 -2.200 4.9 -2.2554.8 -1.852 5.0 -1.8745.0 -1.364 -1.347-.9% ;: -.983;: -.687 5.6 -.694-.322 5.8 -.451z: -.032 6.0 -.2406.5 .395 6.5 .2047.0 .

34、745 .5767.5 1.047 ;:; .9088.0 1.307 8.0 1.1939.0 1.746 9.0 1.65510.0 2.113 10.0 2.03411.o 2.433 I.1.o 2.36112.o 2.712 12.o 2.65Q13.0 2.969 13.0 2.92114.0 3.216 14.0 3.17615.0 3.459 15.0 3.43416.0 3.703 16.0 3.69117.0 3.948 17.0 3.948(b) Leading-Edge SlatProvided by IHSNot for ResaleNo reproduction o

35、r networking permitted without license from IHS-,-,-.NACATN 3007TABLEI.-13COCRDIIWIES OF NACA 64AO1OAIRFOIL, LEADIIIG-EDGESLMl?,ANDDOUBLE-SLOTTED FLAP - Cont&uedStationsd ordtes given from atifoil chord line in percentof airfoil chord(c) Double-Slotted Flap, Main FlapWpper surfaceStation75.00075.15a

36、75.29575.59775.88276.17776.76577.35277.94278.53079.70580.88282.06083.23584.41o85.00086.25090.00095.ocxl100.000)rdinate-1.OQO-.371-.076.286.535.751l.om1.2721.4141.4961.5941.6371.648I-.6301.X3.1.5501.4531.062.541.021Lower surface IStation75.00075.1%75.29575.58775.88276.17776.76577.3%77.94278.53079.705

37、80.88282.06083.23584.41o85.00086.25090.00095.000100.000&Ordinate-1.000-1.557-1.712-1.956-2.095-2.179-2.289-2a71 RO-2.304-2.260-2.136-2.003-1.880-1.762-1.641-1*-1.453-1.062-.541-.021L.E. radius: 0.95 (center on main Iflap chord line)T.E. radius: 0.023 I Provided by IHSNot for ResaleNo reproduction or

38、 networking permitted without license from IHS-,-,-14 NACA TN 3007TABLE I.- cooRD OF NACA 64Ao1o -m, =GEDGE SLAT, ANDlXXIBI&SLOITEDFLAP - ConcludedStationsand ordinates given from vane chord line in percent ofairfoilchord(d) Double-SlottedFlap, VaneUpper surface Lower surfaceStation I Ordinate Stati

39、on Ordinateo 0 0 0.42 .95 -.93.83 1.31 :E -1.141.25 l. 1.25 -1.201.67 1.67 1.67 -1.1.12.08 1.72 2.08 -.852.92 1.74 2.92 -.363.75 1.64 3.75 -.024.58 1.43 4.58 .185.42 1.13 5.42 .276.25 .75 6.25 .257.08 .28 7.08 .11.7.50 0 7.50 0L.E. radius: 1.20 (center on vanechord line)Provided by IHSNot for Resale

40、No reproduction or networking permitted without license from IHS-,-,-.NACA TN 3007TABLEII.- SUMMKhY OFAIRFOIL WITH15CHARACTERISTICSFOR THE NACA 64AO1OVARIOUS HIGH-LII?FDEVICES. R= 6X106Model configurationplain airfoilaAirfoil with split flapaAirfoil with double-slottedflapaAirfoil with leading-edge

41、flap(5 = 300)Airfoil with leadtig-edge flap andsplit flapAirfoil with leading-edge flap anddouble-slotted flapAirfoil with leading-edge slatAirfoil with leading-edge slat andsplit flapAirfoil with leading-edge slat anddouble-slotted flapData from figure 4(a),bIncrementscIncrementsdIncrementsIncremen

42、tsproducedproducedproducedproducedbybybybySn = 00split flapC?nax1.101.882.361.66p-m3.091.942.81ac 1= c kaxdeg11.o I -4-0.7 I 1.26C18.8 I O.%d=1%$=1=$22.0 I 0.84e-+=o. 93e18.20.8710.8 o.72e1. 14C3.08double-slotted flapleading-edge flapleading-edge slat- I-5.7b-10.3C7.8da10. 5d-3 .Ob9.8d-8. 3C=1ll.oeT

43、2.ge-3.810. leProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-# I.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Y&.#v”fkpAb/kr&nendmarehpszwV#WdFigure 1.- Geanetry and reference dimensions for the v

44、erioue Ih-lifiProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. .1.II.,3:,!1I(a) Model with leading-edgeslat and split flap. (b) Model with leading-edgeflap and no trailing- yedge flap.sFigure 2.- Photigra of NACA 6LAO1O airfoil mounted in test eectf

45、on of the Ames 7- by lo-foot wowind tunnel No. 1. z&Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACAq 3007 19.,2420&o-.4./6 -8 0 8 -/6 -8 0 8Section ung/e of oftuck, u , dig(a) R=2and4xloetFigure 3.- Section lift and pitching-moment characteristi

46、csfor the modelwith the leading-edge slat retracted. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-20 NACA IN30072420/.6/.2.8.40-.40-.2-.4-.6-/6 -8 0 8 -/6 -8 0 8.Section ungle of CZVUC%, a , deg(b) R=6=d7 xl,Figure 3.- Concluded.Provided by IHSNot

47、 for ResaleNo reproduction or networking permitted without license from IHS-,-,-NAC!ATN 3007 21CF282420/.6/.2.8.40-.40i -, 2-.4-.61 I 1 fn 1 I I I 1 IFI D 1 1 1 1 1 I E#fF I I Im = + -tii iiim %AJIii iii mv-Q + “ I I I 1I46 -8 0 8 -8 0 8 /6Section ring/e of ottock, a ,deg(a) 5n = 0 and 15,Figure 4.-

48、 Section lift and pitching-moment characteristicsfor the modelwith the leading-edge flap. R = 6 x 106. . . z . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-22 NACA TN 3007Cr3.2282420/.6/.2.8.40-.40-.2-.4-.6-(IIA II III I Vl I IilIEMI I t I I I I, , , II I I u I I II