The Effect of a Flap and Ailerons on the N.A.C.A. M-6 Airfoil Section (1928)
NASA Technical Reports Server (NTRS) · leaf 9
C. A.-M6 AIRFOIL SECTION do .§ 1.2 ?0° .0 \0.8 16° 8 ^•0.4 12° 8° O 10 20 30 40 50 60 70 80 90 100 Per cent span Fig. 16—Lift distribution along span of N. A. C. A. M-6 airfoil with different 4" aileron settings 0° too -4° I 50 -8° 0 -12 \-50 "16° ^-100 10° 20' -20° -10' Flop angle ^-150 Fig.… … 32698 0—29 2
NASA Technical Reports Server (NTRS)
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