A comparison of theoretical and experimental loading on a 63 degrees swept-back wing at supersonic speeds

Victor I. Stevens, John W. Boyd
naca-rm-a9c16
Sep 1949


The pressure distribution over a highly swept wing has been investigated at supersonic speeds to provide data for a comparison of measured and predicted loadings. The wing for the investigation had 63 degrees sweepback of the leading edge, and aspect ratio of 3.5, and a taper ratio of 0.25. The experimental data were obtained for Mach numbers from 1.15 to 1.70 at a Reynolds number of approximately 4.5 million and angles of attack to 10 degrees.

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