1957•Unpublished venueRequires access
A flight investigation to determine the effectiveness of Mach number 1.0, 1.2, and 1.41 fuselage indentations for reducing the pressure drag of a 45 degree sweptback wing configuration at transonic and low supersonic speeds
Willard S. Blanchard, Sherwood Hoffman
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Abstract
Report presenting a flight investigation to determine the effectiveness of three fuselage indentations for reducing the pressure drag of a 45 degree sweptback-wing-body configuration at a range of Mach numbers. The results indicate that the supersonic area rule can be used to determine indentations with low pressure drag over a Mach number range in which the blunt leading edge is subsonic. Information about total drag and pressure drag is provided.