高超声速流动分离-再附产生高热流区的广义模型理论及其应用研究

The large aerothermal loads associated with shock/boundary layer interaction present the scientists and engineers with one of the most serious challenges because they are very difficult to model and predict. Though a great deal of numerical simulations and experimental tests were carried out to study this problem, but a set of systematic theory is still absent. A generalized model will be established with improving the previous theoretical studies of the applicant. The model will be extended to study the typical hypersonic flows with strong shock wave/laminar boundary layer interaction, and the theoretical formulae will be derived to estimate the amplitudes and the locations of peak heat fluxes near the reattachment points. The generalized model will benefit the designer of hypersonic vehicles by disclosing the physics of the shock wave/boundary layer interactions and providing the reliable methods for assessing the peak aero heating in the reattachment regions. This work will contribute to form an engineering theory on the hypersonic separation-reattachment flows with shock/boundary layer and shock/shock interaction.

新型高超声速飞行器研制面临激波/边界层干扰引发的分离-再附问题，预测再附点后形成的高热流区是一个难题。迄今，理论研究大大滞后于数值和实验研究，尚缺乏对峰值热流规律的系统认识。本项目在前期研究的启示下，拟完善高热流区的广义模型，扩展应用于若干包含激波/层流边界层强干扰的流动中，理论导出再附点后峰值热流大小及其位置的解析估算公式，形成一套统一理论框架，供数值计算或工程应用参考。该工作将有助于深入理解激波-边界层相互作用的物理机制，并为建立复杂流动中峰值热流预测的工程理论打下坚实基础。

激波/边界层强干扰可引发高超声速分离-再附流动，如何预测气动加热尤其是预测峰值热流长期困扰着研究者。本项目以理论分析为特色，基于激波/边界层干扰流动的物理特性，提出了再附区“斜驻点-三层结构”模型和预测再附峰值热流的工程理论，以及流动分离的压力干扰-抗干扰模型和分离尺度预测理论，形成完整的分离-再附流动的模型理论框架，并应用于高超声速压缩拐角流动。该理论框架是研究高超声速分离-再附流动的新方案，且拓展性高，应用前景广阔，正是当前航天工程亟需的。本项目还研究了高超风洞来流的振动能激发效应，分析了壁面上振动能适应的微观过程，推导了振动能适应判据，揭示了壁面热流随振动能激发度和壁面适应度的变化机制。进一步的数值结果表明，来流振动能激发对流动分离尺度以及振动能非完全适应壁面的热流均有显著影响，这个新发现值得继续研究。

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