| Re及Ma对边界层的影响分析 |
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| 引用本文： | 王继明.Re及Ma对边界层的影响分析[J].中国科技信息,2011(19):66-66. |
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| 作者姓名： | 王继明 |
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| 作者单位： | 上海飞机设计研究院 |
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| 摘 要： | 本文分析了跨音速流中Ma及Re对边界层的影响,结论为Ma的增加使得激波强度增加,流向逆压梯度增加,边界层厚度增加较快,容易分离;Re的增加有两个效应：一是使得转捩提前,二是使得边界层变薄。R e增加使得激波后机翼表面压力降低,升力损失减小。跨音速范围内,Re对边界层与外流的干扰十分显著。
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| 关 键 词： | 跨音速 边界层分离 激波 |
Analysis of Reynolds and Mach number effects on boundary layer |
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| Abstract: | This paper analyzed the boundary layer in transonic flow.Mach number and Reynolds number effects were taken into consideration.The results were the increase of Mach number increased the shock strength.Boundary layer thickness increased rapidly and resulted in separation.The increase of Reynolds number has two effects: First,make the transition early,and second,make the boundary layer thinner.The increase of Reynolds number decreased the wing surface pressure and made the lift loss lower.Reynolds number have... |
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| Keywords: | transonic boundary layer separation shock transition |
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