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

Description: Report presenting the pressure distribution over a highly swept wing at supersonic speeds to provide data for a comparison of measured and predicted loadings. The wing for this investigation had 63 degrees of sweepback of the leading edge, an aspect ratio of 3.5, and a taper ratio of 0.25. Over the regions influenced by the wing tip and trailing edge, the effects of viscosity apparently are responsible for the poorer agreement between theory and experiment.
Date: September 14, 1949
Creator: Stevens, Victor I. & Boyd, John W.
Partner: UNT Libraries Government Documents Department
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