摘要
为解决前缘钝化后由于外形的变化引起周围流场改变,导致激波形状发生变化而影响飞行器气动特性的问题,对前缘钝化后的吸气式高超声速飞行器气动特性进行了研究。对比分析了前缘钝化对吸气式高超声速飞行器气动特性的影响,得出了吸气式高超声速飞行器气动性能参数随着钝化半径的变化规律。研究结论可为乘波构型的高超声速飞行器一体化设计提供一定的依据。
When the leading edge is blunted,the change of vehicle shape causes the change of the flow field around the vehicle,resulting the change of the shock wave shape,influencing the aerodynamic characteristics of the vehicle. In order to solve this problem,influence of the bluntness on aerodynamic performance of hypersonic vehicle was studied and analyzed. The variation of the hypersonic vehicle aerodynamic characteristics with the bluntness radius was obtained. The results can be used for the integrated design of wave-rider configuration hypersonic vehicle.
出处
《飞行力学》
CSCD
北大核心
2015年第1期21-25,共5页
Flight Dynamics
基金
航天支撑技术基金资助(2013-HT-XGD-014)
中央高校基本科研业务费专项资金资助(3102014KYJD008)
关键词
一体化设计
前缘钝化
激波膨胀波
耦合模型
integration configuration
leading edge bluntness
shock waves and expansion waves
coupling modeling
