Victor I. Stevens, John W. Boyd
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.
An Adobe Acrobat (PDF) file of the entire report: