缝隙内高超声速气动加热数值模拟

Numerical Simulation of Hypersonic Gap Heating

针对航天飞机热防护系统组件之间的缝隙气动加热问题,建立二维缝隙局部网格模型,利用CFD方法研究了二维定常可压缝隙内高超声速气动热环境规律,主要分析了来流攻角、来流马赫数、缝隙宽度、倒角和台阶等因素对流场和气动热环境的影响规律。结果表明上述因素均会对缝隙局部热环境产生影响,在防热设计中应该综合考虑。通过本文的研究工作,给出了一种工程设计中可用的缝隙热环境设计方法。

Aiming at the problem of thermal protection system gap heating of space shuttle, a two dimentional mesh model was established and the technology of computational fluid dynamics （CFD） was adopted to simulate hypersonic gap heating problem. The effect of attack angle, Mach number, gap width, chamfer and step on heat transfer to the gap wall were discussed. The results show that the abovementioned factors affect the gap heating significantly. A method which could be used in engineering design was developed.