Tests of Clark Y wing model to determine distribution of air loads over both wing and flap; tests made at various flap deflections up to 45° and covered range of angles of attack from zero lift to maximum lift for each flap deflection; deflecting partial-span split flap affected pressures and section normal-force and pitching-moment coefficients over entire wing span. (Price 10¢)
Pressure distribution over rectangular airfoil with partial-span split flap
Nat Advisory Committee Aeronautics -- Report
1936
12 pages
Bibliography
Report
Englisch
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Pressure distribution over airfoil with balanced split flap
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