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A note on the effect of heat transfer on peak pressure rise associated with separation of turbulent boundary layer on a body of revolution (NACA RM-10) at a Mach number of 1.61

机译：关于热传递对峰值压力升高的影响的说明，其与马赫数为1.61的旋转体上的湍流边界层分离（NaCa Rm-10）

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Czarnecki, K R; Sinclair, Archibald R;
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年度 1957
页码 1-14
总页数 14
原文格式 PDF
正文语种 eng
中图分类工业技术;
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4. L.R.N. "k-#epsilon#" model. prediction of heat and momentum transfer in turbulent boundary layers, developing under strong pressure gradient conditions [C] . E.V. Shishov, A.I. Leontiev, A.V. Gerasimov International heat transfer conference;IHTC1998 . 1998

机译：L.R.N. “ k-＃epsilon＃”模型。强压力梯度条件下发展的湍流边界层传热和动量传递的预测
5. Similarity analysis for turbulent boundary layers subject to pressure gradient and heat transfer. [D] . Wang, Xia. 2003

机译：受压力梯度和热传递影响的湍流边界层的相似性分析。
6. Adverse-Pressure-Gradient Effects on Turbulent Boundary Layers: Statistics and Flow-Field Organization [O] . Carlos Sanmiguel Vila, Ramis Örlü, Ricardo Vinuesa, -1

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7. Fundamental Studies of Turbulent Boundary Layers with Injection or Suction through Porous Wall : 3rd Report, Investigations on the Separation of Turbulent Boundary Layers in Strong Adverse Pressure Gradients with Injection through Porous Flat Plate [O] . Toshiyuki MAEDA 1972

机译：通过多孔墙喷射或吸入的湍流边界层的基本研究：第3次报告，通过多孔平板注射用注射强度压力梯度分离湍流边界层的研究

A note on the effect of heat transfer on peak pressure rise associated with separation of turbulent boundary layer on a body of revolution (NACA RM-10) at a Mach number of 1.61

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