二维流场、热结构松耦合模拟研究

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。

Numerical Analysis of Two-Dimensional Fluid/Thermal Structure Loosely-Coupled Simulation

In this article,the loosely-coupled method is applied to simulate a two dimensional hypersonic fluid-solid thermally-coupled flow around the leading edge of an axisymmetric flying vehicle. The outer flow field governed by the unsteady Navier-Stokes equations and the inner temperature field governed controlled by unsteady heat-conduction equation are both solved by the commercial code FLUENT.From the differences of results of heat transfer rate,surface temperature,and heat transfer coefficient which were obtained by the loosely-coupled simulation at the same instant but with different forward time steps for outer and inner computations the influence of forward time steps are revealed.Such results have a positive significance for the research of the hypersonic vehicle flying simulation by the loosely-coupled method.