临近空间高超声速滑翔飞行器低雷诺数发汗冷却与两相流动数值研究

The transpiration cooling technique is an important solution for the thermal management of hypersonic gliding vehicles. In the previous research, the performances of transpiration cooling has not been modeling completely. The mechanism of transpiration cooling in the high mach and low Reynolds number flow field has not been studied. For this reason, it is difficult for the transpiration cooling technique to be used to the hypersonic gliding vehicles design. In present work, the factual process of transpiration cooling will be described by modeling the vapor, two-phase and liquid state in flow field. The mechanism of transpiration cooling in the high mach and low Reynolds number flow field will be studied, which shows the effects causing by the factors such as the flow conditions. The work will also show the effect on the aerodynamic characters which causing by transpiration cooling. The transpiration cooling model which can be used to hypersonic gliding vehicle design will be founded. The work will be helpful to the theory of transpiration cooling mechanism and practical application.

对于高超声速滑翔飞行器面临严重的防隔热问题，发汗冷却技术是重要的解决途径。传统发汗冷却研究存在发汗流动建模不全，高马赫数低雷诺数条件下发汗冷却机理认识存在空白的问题，这使发汗冷却应用于飞行器研制存在困难。本项目结合实际发汗过程、外流场影响过程建立多组份-两相流动-相变物理模型完善了发汗问题的模化，通过研究揭示高马赫数低雷诺数条件下耦合外流场的发汗冷却机理、影响敏感因素和发汗对飞行器气动特性的影响规律，最终建立适用高超声速滑翔飞行器整体的发汗冷却模型。拟取得研究成果具有较强的理论意义和工程价值。

本项目建立了多组份-两相流动-相变物理模型和数值模拟方法，实现了发汗过程耦合外流场影响过程的流动模拟。研究获得了高马赫数条件下耦合外流场的发汗冷却机理、影响敏感因素和发汗对飞行器气动特性的影响规律，建立了适用高马赫数飞行器典型部位的发汗冷却模型。取得研究成果可支撑飞行器降热设计。