摘要
采用数值仿真方法,开展了高超声速飞行器(HIFIRE-5)的流场特性计算研究,精确捕捉高超声速流场中的波系、背流面横向流动及表面流动现象,并对激波及横向流动其机理进行了详细分析。结果表明,所用数值计算方法有效,横向流动和横流失稳是产生流场三维涡系结构的主要原因,该认识可为类似外形高超声速飞行器的气动外形设计、优化及气动特性分析提供参考。
The flow field characteristics of hypersonic vehicle HIFIRE-5 has been investigated based on the numerical computational method.The method succeeded in capturing the phenomenon of shock wave system,crossflow transition in the leeward face and surface flow.The mechanism of forming flow structure has also been analyzed simultaneously.The research results indicate that:(1)the numerical method is valid and effective;(2)crossflow and crossflow instability are the main reason of 3Dvortex system in the flow field.The acquisition can provide design reference for hypersonic vehicle configuration design,optimization and aerodynamics analysis.
出处
《宇航总体技术》
2017年第3期33-38,共6页
Astronautical Systems Engineering Technology
基金
国家自然科学基金项目(11372054)
