NASA NACA-RM-L8K22-1949 Two-dimensional wind-tunnel investigation of two NACA 6-series airfoils with leading-edge slats《带有前缘缝翼的NACA第6系列机翼的二维风洞研究》.pdf

《NASA NACA-RM-L8K22-1949 Two-dimensional wind-tunnel investigation of two NACA 6-series airfoils with leading-edge slats《带有前缘缝翼的NACA第6系列机翼的二维风洞研究》.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-RM-L8K22-1949 Two-dimensional wind-tunnel investigation of two NACA 6-series airfoils with leading-edge slats《带有前缘缝翼的NACA第6系列机翼的二维风洞研究》.pdf（46页珍藏版）》请在麦多课文档分享上搜索。

1、0 ! RESEARCH MEMORANDUM TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF TWO NACA 6-SEFXEB AIRFOILS XITH LEADING-EDGE SLATS BY Stanley M. Gottlieb Langley Aeronautical Laboratory Langley Field, Va. I NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS WASHINGTON January 19,1949 Provided by IHSNot for ResaleNo r

2、eproduction or networking permitted without license from IHS-,-,-NACA IIM: No. L#K22 . TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF TWO By Stasley M. Gottlieb .- . An investigation was made in the Langley two-dimensional low- turbulence tunnels of two NACA 6-series airfoils, the NACA %-212 and the m

3、CA 65109, equipped with leading-edge slats and split flaps deflected the other slat parameters, slat depth and width, were mas-med in the “melo Once the optimum configurations vere determined., the slats were attached to the airfoil by four brwketa, one 5 inches from each end of the mdel and one.6 i

4、nches on each side of the mdel center line as shown in figure 2( a) . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-XACA RM No. L-2 5 The tests were conducted in the Langley two-dimensional low-tur- bulence tunnel and in the Lesgley two-dimeneional

5、 low-turbulence pressure tunnel. These tunnel8 have test sections 3 feet wide and 71. feet hi and were designed to test mdels cqletely spanning the 3-foot jet in two-dimensional flow. The tunnele and methods of msasurement are completely described in reference 5 All data were corrected by methods gi

6、ven in reference 5 except lift data obtained in finding the optimun configurations of the lemng-edge slats, which were uncorrected for blocking at high lifts. 2 .Tests were made in the Langley two-dimensional low-turbflence tunnel at a Reynolds number of 2 .O X lo6 to obtain the optimum location of

7、the slats for high mxhmm section lift coefficient uncorrected for blocking at hiTlmum lift coefficient of 0.60 and in angle of attack of 140 were attained with flaps retracted and 0.a and 50 with flaps deflected, and for the NACA A109 airfoil section increases in maxinmn lift coefficient of 0.69 and

8、 in angle of attack of loo were attained with flaps retracted and o .81 and 60 with flaps deflected . (2) Tne split flap was slightly more effective in increasing the gnolds number on the airfoils with leading-edge slats exbended caused the stall to become more gradual. (4) On the MACA 641-2 airfoil

9、 section, for whlch sufficient data were obtained to show optiruum slat location, deflection of the split flap caused the optimum slat location to change in such a way a8 to form a smaller gap between the slat trailing edge and the main part of the airfoil section. (5) Extension of the leading-ed el

10、ats cawed the aerodynamic center to move forward to a point approximately equal to the quarter- chord point of the extended chord. ( 6) The maximum section lift coefficient increased between Reynolds numbers of 2 -0 X 10 and 6.0 X 10 for all configurations tested. As the Reynolds nuniber was increas

11、ed from 6.0 X u3 6 to 9 .O X 10 6 the maximum 6 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM No. L-2 9 section lift coefficient for the NACA 6k1-2l2 airfoil section with split flap deflected 630 and the NACA AlOg airfoil eection remafned

12、 approxl- mately constant, whereas the maxhrm lift coefficient increased sllghtly for the NACA 65109 airfoil section with aplit flap deflected niber, M. J. : Wind-Tunel Tests of Several Forms of Fixed Wing Slot in Conibination with a Slotted Flap on an TI .A .C .A. 23012 Airfoil NACA TN No. 702, 193

13、9 . 4. Seacord, Chmles L.,* Jr., esd Anlrenbruck, Eerman 0. : Effect of Wing Modifications on the Longitudinal Stability of a Tallless All-Wing Airplane Model. MACA ACR No. L5G23, 1945. 5. Von Doenhoff, Albert E., and Abbott, Frank T , Jr : The Langley Two- Dimensional Low-Turbulence Presaure Tunnel

14、 - NACA TN Iio . 1283, 1947. 6- Abbott, Ira H., Von Doenhoff, fibert E ., and Stivers, Louis s., Jr. : sUmma;ry of Airfoil Data. RAGA Rep. No. ! :;e a:;: 50 .ooo 95.013 100.000 F Laver surfaoe 1 1 r t Leading-edge slat Upper surface Station 0 . hd 1.1 7 0689 2.P2 Z:& 11.250 12.500 14.000 f 7 “ . . .

15、 . . . . . . . . . . . . . . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM No. L8K22 TABLE 2 ORDINATES OF HACA 65109 AIRFOIL SECTION mH LEADING-EDGE SUT Statiane ana ordinates in peroent airfoil chard r Leading-edge slat Main part of ai

16、rfoil t - Upper surface T i Upper surface Station Ordinate Station Ordinate St at im lrdinate Station 0 2 138 7.0 2 11.250 12.ogo 12 -93-5 .ooo z.745 . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-“_ 0.6 0.8 . . . Provided by IHSNot for ResaleNo r

17、eproduction or networking permitted without license from IHS-,-,-Slat reference 11, Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. -. . . . , . . . .

18、 . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-* (b) WA 609 airfoil section. ligure 2.- Concluded. Provided by IHSNot for ResaleNo reproduction

19、or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-(a) 8, = 30. Figure 3.- Contours of ahfoil maximum section lift coefficient, uncorrected for blocking at high lifts, for various positions of a 0.140

20、 leadwdge slat on an &A 64+l.5! airfoil section. R = 2.0 x lo6, 4 ? G Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3 Provided by IHSN

21、ot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-&3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . Provide

22、d by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-(c) 6s 43.30. Figure 4.- Continued. . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . . . . . . . . . . . . . . - . . . . -. . . / xg, percent ahmd (

23、d) 6, = 54.30. Figure 4.- Concluded. I. . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . . . . . . . . . (a) 6, = 22O. Flgure 5.- COOUS of alrfoil lnnrirmrm motion lift coefficient, unoorrected for blocking at high 1Vt6, for varioue OSIOII

24、E of a 0.14 slat on an HACA 6309 aFrPoLL section. R = 2.0 x 10 6 . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . . . , . . . . . . . . . . . . . 8 . . . . . . . . . . . . . . . . . . . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . . . - . . . . . . . Q3 . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-