考虑烧蚀表面形貌影响的气动特性精确预示方法  

Study on Numerical Simulation Method of Near Wall Flow on Ablated Rough Surface

作　　者：苏伟[1] 董超[1] 薛普 刘文伶[1] 杨天鹏 Su Wei;Dong Chao;Xue Pu;Liu Wen-ling;Yang Tian-peng(Beijing Institute of Space Long March Vehicle,Beijing,100076)

机构地区：[1]北京航天长征飞行器研究所,北京100076

出　　处：《导弹与航天运载技术（中英文）》2023年第1期21-25,共5页Missiles and Space Vehicles

摘　　要：高速飞行器在飞行过程中防热层烧蚀形成的粗糙表面会影响飞行器的气动特性。针对该问题,对烧蚀表面的近壁流动数值模拟方法进行了研究。采用等效砂粒粗糙度和粗糙函数相结合的方法,对粗糙表面形貌以及对边界层湍流流动的影响进行表征。基于高速粗糙平板风洞试验,开展了3种粗糙壁面湍流模型的数值模拟和验证。最后,以10°尖锥标模外形开展了不同壁面粗糙条件下的流场数值模拟,分析了壁面粗糙对气动特性的影响。研究结果表明,壁面粗糙会对法向力系数、轴向力系数和压心系数产生较大的影响。During the flight of high-speed flight vehicle,the ablation of the heat shield will form rough surface,which will affect the aerodynamic characteristics of the vehicle.The numerical simulation method of near wall flow on ablated surface topography and boundary layer flow is characterized by the combination of equivalent sand roughness and roughness function.Based on the supersonic rough plate wind tunnel experiment,three numerical simulation methods of rough wall turbulence model are used to simulate flow field and be verified.Finally,taking the 10 degree conical standard model as the research object,the flow field simulation under different rough wall conditions is carried out,and the influence of wall roughness on aerodynamic characteristic parameters is analyzed.The results show that the wall roughness has a great impact on the normal force coefficient,the axial force coefficient and the pressure center coefficient.

关 键 词：烧蚀表面 近壁流动 数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]