An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc section and 40 degree sweepback : a pressure-distribution study of the aerodynamic characteristics of the wing at Mach number 1.40

Norman F. Smith, Julian H. Kainer, Robert A. Webster
naca-rm-l51c06
Apr 1951

A pressure-distribution investigation of the wing, in the presence of the fuselage, of a supersonic aircraft configuration has been conducted in the Langley 4- by 4-foot supersonic tunnel at a Mach number of 1.40 and a Reynolds number, based on the mean aerodynamic chord, of 0.598 X 10 (superscript 6).

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