An experimental investigation of the flow phenomena over bodies at high angles of attack at a Mach number of 2.01
Description: Report presenting an investigation in the supersonic pressure tunnel at Mach number 2.01 to study the wake patterns in the lee of bodies at high angles of attack. The configurations tested consisted of two cylindrical body shapes, one circular and one elliptical in cross section, with a fineness-ratio-3.5 ogival nose and a fineness-ratio-6 conical nose. Results regarding vapor-screen photographs, wake characteristics, wake patterns, wake characteristics, and testing with transition strips are included.
Date: October 27, 1955
Creator: Gapcynski, John P.
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Partner: UNT Libraries Government Documents Department