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。
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