A comparison of the experimental and theoretical loading over triangular wings at supersonic speeds

E. Ray Phelps
naca-rm-a50j17
Jan 1953


% A John W. Boyd The results of an experimental investigation of the pressure distribution over two triangular wings at supersonic speeds are presented. The two wings which were tested had identical plan forms, 45 degree sweepback of the leading edge, and an aspect ratio of 4.0, but different airfoil sections.

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