NASA NACA-TN-419-1932 Wind-tunnel tests of the Fowler variable-area wing《福勒可变面积机翼的风洞试验》.pdf

1、ELLIOTT G. REID !CECHNICAL NOTES NATIONAL ADVISORY COl.MITTEE FOR AEROXAUTICS NO. 419 - WIND-TUNXEL TESTS OF THE FOWLER VARIABLE-BBEA WING By Fred E. iVeick and Robert C. Platt Langley Memorial Aeronautical Laboratory Weshington May, 1932 Provided by IHSNot for ResaleNo reproduction or networking pe

2、rmitted without license from IHS-,-,-l c NATIONAL .DVIa range.of slots and angular de- flectiong.of the extension airfoil., . . . APPARATUE! ARD METHOD ,The Fowler wfng.model used in these tests consisted of a basic Clark Y wfngwfth a lo-inch chord and 60-inch span, .and a Clark Y e+ensfcn airfoil h

3、aving a chor.d 40 per centthat of the main w!ng. (6ee figs. 1 and 2 and Table 1.) The extension airfoil and the forward.portfon of the main wing were constructed of laminated mahogany. The rear portion of the main-, therefore, in the tests representing the retracted condition the main wfng was fitte

4、d with a plate covering the-rear 4 Inches of the lower surface. Tests were made with the nose of the extension air- fo3J in nfne positions .(shovn fn fig. 1) covering the range giving the.best slo.tS. At.each of these nose loca- tions the angular deflecf%on.of tkie extenszLon airf,o%l was var,f.ed t

5、hroughout the.required.range. a. ,!. . . .r . . The.7.by 10 foot wind tunnel; A, -Technical Rote.No:.429“ . 3 antes an,d standard test prodedurs in referedce.:2. Be- cause of the high lift obtained %fth.the F , . . - _ Curves of cL max (b ased on the area o.f:the basic . - ding) against-flap angle a

6、re given for each location of the nose of the extensi,dn airfoil in Figures 3 to 5. From the maxrmum values ip these curves contour lfnes were pre- pared which show the various positions gfving the same value of maximum lfft. (Fig. 6.) The value:s,in Figure 6 represent the deflectfon which gave the

7、hfghest value of CL max at each location. . . . . - .: : -“ : r- . . ,I-$ Posftion 5 Basic wing-*- lJ and t cD 1 . a, degrees Fig.11 %,CD and c.p. curves for position 5. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-N.A.C.A. Technical Note No.419 1 Position 6 Basic wing- 2. 2. 2. l-l-%x-l a, degrees Fig.12 Fig.12 %,CD asd c.p. curves for position 6. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-