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首页> 美国政府科技报告 >Study of Normal Shock-Wave Turbulent Boundary-Layer Interactions at Mach Numbers of 1.3, 1.4 and 1.5
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Study of Normal Shock-Wave Turbulent Boundary-Layer Interactions at Mach Numbers of 1.3, 1.4 and 1.5

机译：马赫数为1.3,1.4和1.5的正常冲击波湍流边界层相互作用研究

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This report presents the results of a study of seven flows involving the interaction between a normal shock wave and a two-dimensional turbulent boundary layer. The measurements were made at free-stream Mach numbers of 1.3, 1.4 and 1.5 and at Reynolds numbers based on an effective streamwise run of 10 to 30-million. The results were obtained from comprehensive traverses with both pilot and static probes. Standard boundary-layer integral parameters based on wall and measured static pressures are presented, together with velocity profiles and the Mach number distribution over the interaction region. An investigation has been made of the 'law of the wall' and the 'law of the wake' under the influence of strong normal pressure gradients.

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