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本文针对轴对称型飞行器前缘部位,采用松耦合方法,开展了二维高超声速流固界面的热耦合计算。满足非稳态N-S方程的外部流场和内部非稳态热传导均采用商用软件FLUENT进行计算。通过对相同时刻,不同松耦合推进时间步长引起的壁面热流密度、壁面温度、表面传热系数的差异对比,得出了松耦合推进时间对以上参数的影响规律,这对有效实施松耦合方法进行高超声速飞行器模拟具有积极意义。
Aiming at the leading edge of the axisymmetric aircraft, a loose coupling method is used to calculate the thermal coupling of two-dimensional hypersonic fluid-solid interface. The external flow field and the internal non-steady-state heat conduction that satisfy the unsteady N-S equation are calculated using the commercial software FLUENT. By comparing the difference of wall heat flux density, wall temperature and surface heat transfer coefficient caused by different loosely coupled propulsive time steps at the same time, the influence law of loosely coupled propulsion time on the above parameters is obtained, which is significant for the effective implementation of loosely coupled method Hypersonic aircraft simulation has positive significance.