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导弹在运载器尾腔内的点火分离，涉及高温、高压气体在喷管和运载器尾腔内的三维非定常流动。采用分步显式和隐式ＮＮＤ格式对轴对称和三维多喷管非定常亚、跨、超混合喷流流场进行数值模拟，单喷管导弹的喷管流动和尾腔流动使用整体轴对称流动模型；对于多喷管导弹，喷管流动使用轴对称流动模型，尾腔流动为三维流动模型，喷管与尾腔流动间由边界参数进行耦合。算例表明，该方法能较好地捕获喷管和尾腔流动中的三维运动激波，计算结果与实验符合良好。
The separation of the missiles by the missile in the tail cavity of the vehicle involves the three-dimensional unsteady flow of high-temperature and high-pressure gas in the nozzle and the tail cavity of the carrier. The stochastic and implicit NND schemes are used to simulate the unsteady subsonic, cross-and super-mixed jet flow fields of the three-dimensional multi-nozzle. The nozzle flow and the tail cavity flow of the single-jet missile use the overall axial symmetry Flow model. For multi-nozzle missiles, the nozzle flow uses an axisymmetric flow model, the tail cavity flow is a three-dimensional flow model, and the nozzle and tail cavity flow are coupled by boundary parameters. The experimental results show that the proposed method can capture the 3D shock waves in the nozzle and tail cavity well, and the calculated results are in good agreement with the experimental results.