Investigation made to study possibility of preventing shock-induced separation on wing with plain flap through use of area suction, and hence of reducing drag of wing; data obtained at R of 2.9×106 for range of Mach numbers from 0.70 to 0.84 with different suction area configurations.
Tests of area suction flap on NACA 64A010 airfoil at high subsonic speeds
NASA -- Tech Note
1960
43 pages
Report
English
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Boundary-layer and stalling characteristics of NACA 64a010 airfoil section
Engineering Index Backfile | 1950
|Engineering Index Backfile | 1950
|Engineering Index Backfile | 1949
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