基于非线性耦合本构关系模型的尖化前缘气动加热影响研究  

RESEARCH ON THE AERO-HEATING AT THE SHARPENED LEADING EDGE BASED ON NONLINEAR COUPLED CONSTITUTIVE RELATIONS

作　　者：杨俊沅 李旭东[2] 曾舒华 赵文文[1] 张赋 陈伟芳[1] Yang Junyuan;Li Xudong;Zeng Shuhua;Zhao Wenwen;Zhang Fu;Chen Weifang(School of Aeronautics and Astronautics,Zhejiang University,Hangzhou 310027,China;Beijing Institute of Space Long March Vehicle,Beijing 100076,China)

机构地区：[1]浙江大学航空航天学院,杭州310027 [2]北京航天长征飞行器研究所,北京100076

出　　处：《力学学报》2023年第10期2321-2330,共10页Chinese Journal of Theoretical and Applied Mechanics

基　　金：国家自然科学基金(92271114,92271204,U20B2007和12002306);中央高校基本科研业务费(226-2022-00172)资助项目.

摘　　要：结合数值模拟与风洞试验技术,在高超声速连续/稀薄滑移流条件下对尖化前缘这一典型构型的气动加热影响开展深入研究.在三维有限体积框架下,应用非线性耦合本构关系(nonlinear coupled constitutive relations,NCCR)模型对试验工况下的尖化前缘外形开展数值计算,检验NCCR模型在尖化前缘构型中准确描述局部稀薄非平衡流动和物面气动热的性能.数值结果与实验数据对比表明,在等效高度33 km的风洞试验条件下,NCCR模型计算得到的驻点热流系数峰值同实验值偏差为1.81%,Fay-Riddell公式和纳维−斯托克斯(Navier-Stokes,NS)方程得到的驻点热流系数峰值同实验值偏差均在5%以内,物面其他位置的壁面热流系数计算值与实验值偏差均在10%以内,证明此时飞行器尖化前缘区域局部稀薄气体效应对气动加热影响程度较弱;在等效高度60 km时,飞行器尖化前缘区域附近的局部稀薄气体效应对气动加热的影响较为明显,NS方程计算的驻点热流系数偏差为33.31%,Fay-Riddell公式计算驻点热流系数同实验值偏差为29.5%,NCCR模型计算的驻点热流系数与实验值的偏差为11.77%.体现出NCCR模型求解稀薄非平衡流动的优势.The aerodynamic heating effect of a representative sharpened leading-edge model under hypersonic continuous/rarefied flow conditions is investigated through the integration of numerical simulation and wind tunnel testing methodologies in this study.Based on a three-dimensional finite volume framework,the sharpened leading-edge model is numerically analyzed using the nonlinear coupled constitutive relations(NCCR)model,facilitating the accurate representation of local rarefied non-equilibrium flow and surface heat flux.The performance of the NCCR model in describing the sharpened leading-edge is evaluated and corroborated in comparison with the experimental data.Under wind tunnel test conditions at an equivalent altitude of 33 km,it is observed that the discrepancy between the peak heat flux coefficient at the stagnation point computed by the NCCR model and the experimental data is a mere 1.81%.Moreover,the peak heat flux coefficient at the stagnation point obtained by the Fay-Riddell formula and the Navier-Stokes(NS)equations is within 5%according to the experimental value,the coefficient of heat flux at other locations on the surface is also well maintained from the experiment value,i.e.,the deviations is within a range of 10%,which proves that the local rarefied gas effect near the sharpened leading-edge of the aircraft has a weak effect on aerodynamic heating.In contrast,at an equivalent altitude as high as 60 km,the effect of local rarefied gas near the sharpened leading-edge on aerodynamic heating is obvious,and the deviation between the coefficient of heat flux at the stagnation point with the help of the NS equations and the experimental data amounts to 33.31%.The deviation of the peak heat flux coefficient at the stagnation point calculated by the Fay-Riddell formula is 29.5%in terms of the experimental value.However,the variation in stagnation heat flux coefficient obtained from the NCCR model remains comparatively low at 11.77%.It shows the advantage of the NCCR model for solving rarefied nonequilibrium

关 键 词：高超声速流动 风洞试验 非线性耦合本构关系 尖化前缘 气动加热 

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]