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Preliminary wind-tunnel tests of triangular and rectangular wings in steady roll at Mach numbers of 1.62 and 1.92

Clinton E. Brown, Harry S Heinke

Abstract

Damping-in-roll coefficients for a series of triangular plan-form wings and two rectangular plan-form wings have been obtained from supersonic-tunnel tests. The wings were mounted on a body of revolution and tested at Mach numbers of 1.62 and 1.92.

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Key concepts: Mach number, Supersonic speed, Wind tunnel, Supersonic wind tunnel, Series (stratigraphy), Wing, Mechanics, Angle of attack