Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : investigation at a Mach number of 1.53 to determine the effects of cambering and twisting the wing for uniform load at a lift coefficient of 0.25

Robert T. Madden
May 1949

Tests have been performed at a Mach number of 1.53 with a wing-fuselage combination having a wing with 63 degrees leading-edge sweep, aspect ratio of 3.46, and a taper of 0.25. This wing had an NACA 64A005 thickness distribution parallel to the plane of symmetry and was combered and twisted. The principal object of the investigation was to determine the effects of camber and twist on the maximum lift-drag ratio and pitching-moment characteristics.

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