不同气体模型与滑移边界模型下升力体摩阻热流预测  

Friction and heat flux prediction of lift body under different gas models and slip boundary models

作　　者：严攀 李沁 黄潇 郭晓明 翁谊辉 尤延铖 YAN Pan;LI Qin;HUANG Xiao;GUO Xiaoming;WENG Yihui;YOU Yancheng(School of Aerospace Engineering,Xiamen University,Xiamen 361000,China;Science and Technology on Space Physics Laboratory,China Academy of Launch Vehicle Technology,Beijing 100076,China)

机构地区：[1]厦门大学航空航天学院,厦门361000 [2]中国运载火箭技术研究院空间物理重点实验室,北京100076

出　　处：《北京航空航天大学学报》2025年第4期1277-1291,共15页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：针对高超声速升力体外形的摩阻、热流预测问题,采用所发展的三阶精度本质无波动格式,研究了不同气体模型(完全气体、平衡气体)、滑移边界模型(M-S、Le)和来流条件(高度、马赫数和壁面温度)对摩阻、热流等预测的影响。研究采用不同滑移边界模型和气体模型,对双马赫反射问题及典型高超声速绕流问题绕流进行了数值模拟与分析。结果表明:高保真气体模型、滑移边界模型和高精度计算格式能够使高超声速问题计算具有更好的精度。在此基础上,开展了不同高度、马赫数和壁温的高超声速升力体绕流数值模拟与分析,综合分析了滑移边界模型和气体模型对摩阻、热流等预测的影响。结果表明:不同气体模型之间的结果存在较大差异,平衡气体模型预示的边界层温度更低、边界层厚度更小、壁面热流更大、摩阻系数与总阻力系数稍大,二者差异随高度增加而增大;完全气体模型下,不同滑移边界模型总阻力系数、压心位置和热流分布均存在差异且随高度增加差异有所增大;采用平衡气体模型时,不同滑移模型之间预测结果相近。In view of the friction and heat flux prediction problems in the hypersonic flows around a lift body,the influence of different gas models(perfect gas and equilibrium gas),slip boundary models(M-S and Le),and incoming flow conditions(height,Mach number,and wall temperature)on the prediction of friction and heat flux was studied with the developed third-order weighted essentially non-oscillatory scheme.Firstly,numerical simulation and analysis of double Mach reflection problem and typical hypersonic examples were carried out by different slip boundary models and gas models.The results show that high-fidelity gas models,slip boundary models,and highprecision schemes show better accuracy in the calculation of hypersonic problems.On this basis,numerical simulation and analysis of hypersonic flows around a lift body at different heights,Mach numbers,and wall temperatures are carried out.The effects of slip boundary models and gas models on the prediction of friction and heat flux are comprehensively analyzed.The results show that different gas models are quite different,and the equilibrium gas model gets lower temperature in the boundary layer,smaller thickness of the boundary layer,greater wall heat flux,and slightly larger friction coefficient and total drag coefficient.The difference between the two gas models increases with the increase in height.Under the perfect gas model,the total drag coefficient,position of the center of pressure,and heat flux distribution of different slip boundary models show greater difference,which increases with the increase in height.Under the equilibrium gas model,the results of different slip boundary models are similar.

关 键 词：高超声速 升力体 滑移边界条件 平衡气体 热流 摩阻 

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] V411