Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effect of Reynolds number at supersonic Mach numbers on the longitudinal characteristics of a wing twisted and cambered for uniform load

John C. Heitmeyer
naca-rm-a50g10
Oct 1950


Results of a wind-tunnel investigation of the longitudinal characteristics of a wing-body combination employing a wing with leading edge swept back 63 degrees are presented. The model wing, which was cambered and twisted to support a uniform load at a lift coefficient of 0.25 at a Mach number of 1.53, had an aspect ratio of 3.5 and a taper ratio of 0.25.

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