The Effect of a Flap and Ailerons on the N.A.C.A. M-6 Airfoil Section (1928)
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model was 6.00. Figures 5 and 6 show the true polar (lift and drag coefficient to the same scale) curves for the tests with the flap and with the ailerons, respectively; Figures 7, 8 and 9, 10 show the lift and drag coefficients plotted against the angle of attack. The effect of flap or aileron… … Fig. 3.—N. A. C. A. M-6 airfoil with flaps 20° down Fig. 4—N. A. C. A. M-6 airfoil with ailerons displaced 20° with angle of attack, a, jrp for the various conditions is practically constant, verifying that the of an airfoil is independent, or nearly independent of the shape of the section. Figure…
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