Results indicated that larger flap would provide greater lift increments but would lose lift effectiveness at higher deflections and at lower angle of attack than would smaller flap.
Wind-tunnel investigation of NACA 0009 airfoil with 0.25- and 0.50-airfoil-chord plain flaps tested independently and in combination
Nat Advisory Committee Aeronautics -- Tech Note
1948
34 pages
Report
Englisch
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Engineering Index Backfile | 1948
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