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高超声速飞行器处于高空高速飞行环境,表面气动加热现象十分严重。有效预测并降低飞行器的表面温度,对防热材料和结构提出要求是高超声速飞行器设计的一个关键问题。采用三维N-S方程、Mac-Cormack中心差分格式对类乘波体构型的高超声速飞行器全机气动加热进行了数值研究。分析了不同马赫数来流对气动加热的影响。研究结果表明,采用的数值计算方法能够较清晰地预测类乘波体高超声速飞行器全机气动加热温度分布情况,所得结果可为高超声速飞行器的防热材料选取和热防护系统设计提供参考。
Hypersonic aircraft in high-altitude high-speed flight environment, surface aerodynamic heating is very serious. Effectively predicting and reducing the surface temperature of aircraft, making demands on heat-resistant materials and structures is a key issue in hypersonic vehicle design. A three-dimensional N-S equation and the Mac-Cormack central difference scheme are used to numerically study the whole-body aerodynamic heating of a hypersonic vehicle with a class-by-wave structure. The effects of different Mach numbers on the aerodynamic heating were analyzed. The results show that the numerical calculation method can predict the whole temperature distribution of the aerosols in the class-spacecraft hypersonic vehicle more clearly, and the results can provide a reference for the selection of the heat-protection material and the design of the thermal protection system for the hypersonic vehicle.