全域气动仿真工具在高超飞行器设计中的应用  

Application of Full range Aerodynamic Simulation Tool in Hypersonic Vehicle Design

作　　者：吕凡熹 左光[1] 石泳[1] 李正洲 余雄庆[3] 肖天航[3] LV Fan-xi;ZUO Guang;SHI Yong;LI Zheng-zhou;YU Xiong-qing;XIAO Tian-hang(Qian Xuesen Laboratory of Space Technology,China Academy of Space Technology,Beijing 100094,China;China Aerodynamics Research and Development Center,Mianyang 621000,China;College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]中国空间技术研究院钱学森空间技术实验室,北京100094 [2]中国空气动力研究与发展中心,四川绵阳621000 [3]南京航空航天大学航空学院,江苏南京210016

出　　处：《航空计算技术》2020年第6期18-21,26,共5页Aeronautical Computing Technique

基　　金：国家自然科学基金项目资助(11802015)。

摘　　要：结合工程分析方法与快速数值计算方法,开发了一种面向飞行器概念设计阶段的直角全速域气动仿真工具。工具直接利用几何外形输出的文件格式,高度自动化生成流场计算需要网格。在流场计算方面:1)对于亚声速,采用基于自适应直角网格的有限体积法求解全速势方程;2)对于跨/超声速,采用基于自适应直角网格的有限体积法求解欧拉方程;3)对于高超声速,采用机翼牛顿撞击理论的工程面元法。上述3种方法均加入粘性修正。应用上述气动工具考察了一个通用高速飞行器在宽速域下的气动性能,并且将计算数据与高精度数值模拟方法的数据进行对比。相关对比结果表明,气动工具自动化程度高、求解精度良好,可作为高超飞行器设计阶段总体布局选型、气动外形优化的工具。Combining engineering analysis method and fast numerical simulation method,a rapid aerodynamic analysis tool for flight vehicle conceptual design was developed in this paper.The flow field grid could be highly automatic generated based on flight vehicle geometry output file.Three methodologies were integrated in this tool for flow field solution:1)a finite volume full potential method on adaptive cartesian girds for subsonic flow;2)a finite volume Euler method on adaptive cartesian girds for transonic and supersonic flow;3)an engineering panel method for hypersonic flow.The aerodynamic performance of a general high speed vehicle in a wide speed range was investigated by using this tool,and the results were compared with those of the high precision numerical simulation method.The comparison indicated that the aerodynamic analysis tool had highly automation and a good solution accuracy,which could be used as a tool for the overall layout selection and aerodynamic shape optimization of hypersonic vehicle in the design phase.

关 键 词：概念设计 空气动力学 全速势方程 欧拉方程 工程面元法 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]