Supercritical airfoil drag reduction by passive shock wave/boundary layer control in the Mach number range .75 to .90
23rd Aerospace Sciences Meeting ; 1985 ; Reno , NV , U.S.A.
1985-01-01
Conference paper
Electronic Resource
English
Passive drag reduction on a complete NACA 0012 airfoil at transonic Mach numbers
Tema Archive | 1987
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