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对飞船再入舱高超声速化学非平衡三维流场进行数值模拟。控制方程为含化学反应源项的全Ｎａｖｉｅｒ－ Ｓｔｏｋｅｓ 方程组， 化学模型为高温空气的七组元模型， 其组元成分为Ｎ２ 、Ｏ２、ＮＯ、Ｎ、Ｏ、ＮＯ＋ 、ｅ－ 。差分格式采用张涵信院士提出的ＮＮＤ激波捕捉格式并用全耦合方法处理流动方程及化学反应方程， 对化学反应源项采用全隐式处理， 运用时间预处理技术以加快收敛。同时， 也对完全气体模型进行计算， 以分析真实气体效应。与实验数据对比， 说明本文结果是可信的。
The hypersonic chemical non-equilibrium three-dimensional flow field in the reentry spacecraft was numerically simulated. The governing equations are all Navier-Stokes equations with chemical reaction source terms. The chemical model is a seven-element model of high-temperature air with components of N2, O2, NO, N, O, NO +, e-. The differential format adopts the NND shock capture format proposed by academician Zhang Hanxin and treats the flow equation and chemical reaction equation with the full coupling method. The chemical reaction source term is implicitly processed and the time preprocessing technique is used to accelerate the convergence. At the same time, a complete gas model is also calculated to analyze the real gas effect. Compared with the experimental data, the results of this paper are credible.