The Effect of a Flap and Ailerons on the N.A.C.A. M-6 Airfoil Section (1928)
NASA Technical Reports Server (NTRS) · leaf 11
the lift, displacing the flap produced a smaller change in the moment coefficient than the change indicated by the theoretical calculation, especially for large flap displacement angles. The moment coefficient as determined from the tests is in agreement with the theory inasmuch as it is… … Fig. 24.—Flow pattern around airfoil at theoretical angle of zero lift air stream corresponding to the computed angle of zero lift. The resulting pattern, a photograph of which will be found in Figure 24, reveals at once the reason for the discrepancy between the observed and com- puted angles of…
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