A transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2. : wing-fuselage configuration having a wing of 0 degrees sweepback, aspect ratio 4.0,taper ratio 0.6, and NACA 65A006 ai

Cahn, Maurice S Bryan, Carroll R
naca-rm-l51a02
March 06, 1951


No Abstract Available

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