Abstract
A brief description of the flow field is given for the interaction of shock wave and laminar boundary layer on a compression corner in supersonic flow. A special sub-case—that of leadingedge laminar separation—is anafyzed by extension of Chapman's laminar mixing-laj^er theory. Results are tabulated for ranges of Mach number 1 < M0 < 10, and compression-corner angle 0 < /3 < 45°. A limited region of possible leading-edge laminar separation with an attached leading-edge shock (or in certain cases an expansion) followed by a second shock due to the reattachment flow is found to exist. Comparison with existing experimental data is found to be satisfactory in several cases.
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