摘要
为了弄清典型高超声速飞行器再入时处于连续区的流场状态,采用多组分、考虑非平衡态气体振动激发与化学反应过程的守恒型Navier-Stokes方程组,并用高分辨率TVD格式进行求解,获得了不同飞行工况下飞行器流场的气动热力学(尤其是壁面热流密度)和热-化学非平衡态特性,数值结果与风洞试验及飞行数据吻合较好.通过对多个工况点下流场状态的分析与对比,给出了高超声速飞行器在整个再入过程中的壁面热流密度值、气动力系数,尤其是计算域内热力学非平衡区的分布特性,这对有效地完成飞行器热防护设计具有积极意义.
Several typical hypersonic vehicle flowfields are simulated by using the conservation form of Navier-Stokes equations with multi-species,nonequilibrium molecular thermal excitation and chemical reactions based on the high-resolution TVD scheme.The aerothermodynamic properties（such as convective heat flux） and the thermo-chemical nonequilibrium phenomenon of hypersonic-continuum flowfields are obtained during reentry trajectory,and these results are in good agreement with experiment and flight data.By analyzing and comparing the difference of the hypersonic vehicle reentry flowfields in multiple cases,the predictive results,such as wall heat flux,aerodynamic-force coefficients,particularly the thermal nonequilibrium areas in the computational domain,are achieved to benefit the design of vehicle thermal protection system.
出处
《西安交通大学学报》
EI
CAS
CSCD
北大核心
2010年第1期71-76,共6页
Journal of Xi'an Jiaotong University
基金
国家自然科学基金资助项目(50376004)
教育部高等学校博士学科点专项科研基金资助项目(20030007028)
关键词
多工况
高超声速飞行器
再入
气动热力学
非平衡态
multiple cases
hypersonic vehicle
reentry
aerothermodynamics
nonequilibrium
