Above some altitude within atmosphere layer, the boundary layer on after body will separate due to plume.
在大气层某一定的高度以上，火箭后体上的边界层将会由于羽流引起分离。
An engineering model for hypersonic reentry body trail is established in this paper, and a calculation is performed by using boundary layer theory.
建立了再入体再入大气层形成的尾迹的工程模型，并运用边界层理论求解二维等压湍流尾迹流动。
According to the boundary layer character in reentry wake of hypersonic blunt cone body, this paper presents a local similar solution for hypersonic wake.
依据钝锥体再入远尾迹流动的边界层特征，从边界层方程出发得到了高超声速远尾迹流动的拟相似性解。
According to Belotserkovskii's method, using a series expansion and boundary layer method, an analytical solution for axisymmetric 'hypersonic flow over a flat-headed body has been obtained.
根据方法，使用级数展开和附面层方法，得到了轴对称高超音速绕流平头物体的一个解析解。
The electromagnetic body force was used to change the configuration of the boundary layer of flow.
利用电磁体积力改变流体边界层的结构，用作用于流体边界层上的电磁力进行消涡与增涡控制。
The electromagnetic body force was used to change the configuration of the boundary layer of flow.
利用电磁体积力改变流体边界层的结构，用作用于流体边界层上的电磁力进行消涡与增涡控制。
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