1972•Journal of Fluid MechanicsRequires access

Heat transfer from hypersonic turbulent flow at a wedge compression corner

G. T. Coleman, J. L. Stollery

Abstract

A hypersonic gun tunnel has been used to measure the heat-transfer-rate distribution over a compression corner under turbulent boundary-layer conditions. Attached, incipient and separated flows are considered. The results are compared with other experimental data and with the predictions of a simple theory.

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Key concepts: Mechanics, Boundary layer, Wedge (geometry), Turbulence, Hypersonic speed, Heat transfer, Materials science, Compression (physics)