Pressure Distribution Over a Symmetrical Airfoil Section with Trailing Edge Flap (1931)
NASA Technical Reports Server (NTRS) · leaf 13
12 REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS … Figure 25.—Normal force coefficient versus flap angle at different Figure 24.—Theoretical parameters (independent of aspect angles of attack; 10 per cent c flap. Reynolds Number 0.356X10^ ratio)
NASA Technical Reports Server (NTRS)
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