摘要
基于气体动理学方法(gas kinetic scheme,GKS)分别从单独流场和流固耦合两方面开展了针对支杆结构热防护系统的数值模拟研究。首先利用二维标准圆管模型验证算法在单独流场计算中的可靠性,然后通过比较不带支杆和带支杆情形下圆管外壁面的气动热特性及相应流场特征,分析得到支杆降热的有效性及其降热机理。接着在将GKS应用到流场/结构温度场耦合模拟并进行验证后,进一步分析流固耦合作用下的支杆降热性能,结果发现支杆的降热效果随着流固耦合时间的推进不断增强,从而有利于高超声速飞行器长时间巡航飞行。
Based on the gas kinetic scheme(GKS),numerical simulation research on the thermal protection system with the spike was carried out from the independent flow field and the fluid-structure interaction.The reliability of the algorithm in independent flow field was first verified by using the standard cylindrical model,and then the effectiveness and mechanism of the heat reduction of spike were analyzed by comparing the aerothermal characteristics and the corresponding flow field characteristics of the cylindrical model without/with the spike.After verification by applying GKS to the coupled simulation of flow field/structure temperature field,the heat reduction performance of spike under the fluid-structure interaction was further analyzed.The results show that the heat reduction performance of spike increases with the advancement of the fluid-structure interaction time,which is beneficial to the long-term cruise flight of the hypersonic vehicle.
作者
柳昌亚
周迪
陆志良
郭同庆
LIU Chang-ya;ZHOU Di;LU Zhi-liang;GUO Tong-qing(Key Laboratory of Unsteady Aerodynamics and Flow Control,Ministry of Industry and Information Technology,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《气体物理》
2023年第3期46-54,共9页
Physics of Gases
基金
国家自然科学基金(11872212,12102187)
江苏省高校优势学科建设工程资助项目。
关键词
气体动理学方法
流固耦合
支杆
降热
高超声速流动
gas kinetic scheme
fluid-structure interaction
spike
heat reduction
hypersonic flow
