NASA NACA-TN-2288-1951 Estimation of low-speed lift and hinge-moment parameters for full-span trailing-edge flaps on lifting surfaces with and without sweepback《带有或不带后掠角升力面且全翼展后缘襟翼.pdf

《NASA NACA-TN-2288-1951 Estimation of low-speed lift and hinge-moment parameters for full-span trailing-edge flaps on lifting surfaces with and without sweepback《带有或不带后掠角升力面且全翼展后缘襟翼.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-TN-2288-1951 Estimation of low-speed lift and hinge-moment parameters for full-span trailing-edge flaps on lifting surfaces with and without sweepback《带有或不带后掠角升力面且全翼展后缘襟翼.pdf（48页珍藏版）》请在麦多课文档分享上搜索。

1、C C G C z E c z C sc because it is impossible to measure it experimentally by direct means. However, theremaining factors in the above equation can be measured experimentally, enabling the determination of results presented in figure 10 show that much / pseudo-experinrental values of is (A%)sc 1 The

2、 better agreement with the obtained by the FaUmer Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-i 8 NACA TN 2288 theo (method 1) than by the theory of references 2 and 10 (method 4), especially for modsls having large angles of sweepback. Since the

3、 computation of the induced-camber correction to chc, by the Falkner method is rather involved, design charts (figs. 11 and 12) are presented so that these values may be determined directly for flap- chord ratios from 0.20 to 0.40, for aspect ratios from 2 to 6, and for airfoils having up to 45 of s

4、weepback. flap-chord ratios for the swept-back models were taken in the plane perpendicular to the 0.25-chord line. are desired using the flap-chord ratio measured in the plane of sym- metry, the equivalent ratio perpendicular to the 0.25-chord line should be computed and used in the charts.) It sho

5、uld be noted that the (If the values of The application of the method is presented in detail in the appen- The results obtained by this procedure are presented in figure 2, dix. Application to method 3.- This method combines the induced angle- of-attack corrections of method 2 with the induced-cambe

6、r correction to 4 and C in the equation for (A%)sc CL gives cLa c= (0.108) (0.707) 1 + (6.188)(0.108)(0.707) + 0.0760 = 0.0493 Similarly, the equation of reference 4 for Ck become s The use of cos A cos Ah instead of cos2 A, and of cos h instead of the effects of taper by considering the effective c

7、hange in the flap deflection to be a function of the sweep of the hinge line rather than the sweep of the guarter-chord line. Tq evaluate (1 -:) for use in the preceding equation cos A, is an approximation suggested in reference 10 to account for and T Wind-Tunnel Inveqtigation of Horizontal Tails.

8、I - Unswept and 35 Swept-Back Plan Forms of Aspect Ratio 3. NACA RM A7x24, 1948. I1 - Unswept and 35O Swept-Back Plan Forma of Aspect Ratio 4.5. NACA RM A8Bl1, 1948. I11 - Wswept and 35O Swept-Eack Plan Forms of Aspect Ratio 6. NACA RM A8Q0, 1948. IV - Unswept Plan Foh of Aspect Ratio 2 and a Two4im

9、ensional Model. NACA RM A8J21, 1948. V - 45 Swept-Back Plan Fom of Aspect Ratio 2. NACA RM A9Do5, 1949 0 8. Crane, Robert M.: Computation of Hinge-Moment Characteristics of Horizontal Tails from Section Data. NACA CB 5BO5, 1945. 9. DeYoung, John, and Harper, Charles W.: Theoretical Symmetric Span Lo

10、ading at Subsonic Speeds for Wings Having Arbitrary Plan Form. NACA Rep. 921, 1948. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN 2288 21 10. Toll, Thomas A., and Schneiter, Leslie E.: Approximate Relations NACA TN 1711, 1948. for Hinge-Mom

11、ent Parameters of Control Surfaces on Swept Wings at Low Mach Numbers. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-k 0 R NACA TN 2288 T 0 d t i t c Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-

12、NACA TN 2288 . 23 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2+ 2 4 2 hi IC, 1 - 9iZE -2 Qv) E2 NACA TN 2288 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA 5 2 c u C . 9 u) E 5 . P Provided

13、 by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-26 NACA TN 2288 c K 9 P Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN 2288 27 .06 .04 .02 0 .06 I .04 CLs .02 I 2 3 4 5 6 Aspect ratio, A . (0) Lift p

14、arameters. 0 Figure I,- Comparison of the experimentof /Iff and hinge-moment parameters as a function of the aspect ratio with those calculated by Method I. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-P F/gUre l. -Concluded. 3 4 5 6 Aspect roijo,

15、 A Hinge-moment poromeiers. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-29 NACA TN 2288 , .08 .06 .O 4 .02 0 .06 .04 * 02 0 t (a) Lift parameters. Figure Z.-Cornparison of the experlmental lift and hhge-moment parameters as o function of the_ aspect ratio with those cafculoted by Method 2. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-