类乘波体飞行器气动加热的工程计算方法

Engineering Calculation of Aerodynamic Heating for Quasi-waverider Vehicle

针对类乘波体总体优化设计的需要,采用参考温度法和经验公式,计算了类乘波体飞行器在助推段和巡航段的气动加热.利用气动加热、蒙皮表面热辐射以及蒙皮内部热传导建立了热流量方程,求出了机身驻点和机翼前缘在助推段的温度-时间历程,以及巡航段内机身机翼迎风面中心线上的温度分布.结果表明,助推段驻点温度上升很快,在巡航一段时间后温度逐渐达到平衡;沿机身方向边界发生转捩,转捩区内温度增加,高马赫数可推迟转捩点,大攻角则提前转捩点.该方法可应用于高超声速类乘波体飞行器的概念研究和多目标优化设计.

Aiming at the need of integral optimization design of quasi-waverider vehicle （QWV）, its aerodynamic heating at boosted and cruise periods was studied based on reference temperature and experience formula. With the aerodynamic heating, thermal radiation and heat conduction of skin, heat flow rate equation was built. By solving this equation, the wall temperature-time relationship of body stagnation and wing leading edge at boosted period, the wall temperature distribution of windward side of body and wing center line at cruise period were obtained. The results show that the temperature of body stagnation region increases rapidly at boosted period, and it will come to balance after entering cruise period. Along body axis direction, boundary layer transition appears, which increases wall temperature. A high Math number can postpone transition position, and big angle of attack will advance the transition position. This method can be applied to pre-research and multi-objective optimization design of hypersonic QWV.