Force, moment, and pressure-distribution characteristics of rectangular wings at high angles of attack and supersonic speeds
Description: Report presenting experimental force and moment data for rectangular wings of aspect ratios 1, 2, and 3 at a range of angles of attack and Mach numbers. Shock-expansion theory was found to adequately predict the span load distribution in the two-dimensional flow region below the shock-detachment angle. Results regarding basic physical data, the attached regime, and the detached regime are provided.
Date: February 13, 1956
Creator: Pitts, William C.
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Partner: UNT Libraries Government Documents Department