Effect of trailing edge thickness on lift at supersonic velocities

Dean R. Chapman, Robert H. Kester
naca-rm-a52d17
Jul 1952


Measurements of lift were made on various rectangular-plan-form wings differing in trailing-edge thickness, profile shape, maximum thickness ratio, and aspect ratio. The experiments were conducted at Mach numbers between 1.5 and 3.1, at Reynolds numbers between 0.55 and 2.2 million, and on wings with and without boundary-layer trips. The measurements are compared to theoretical calculations based on both second-order and shock-expansion theory. Calculated results using shock-expansion theory are presented for Mach numbers between 1.5 and 10.

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