一种曲面压缩高超声速进气道的设计及流场快速求解方法  

Rapid design and flow field solution method of curved compression hypersonic inlet

作　　者：王鑫 袁化成[1] 刘甫州 张锦昇 WANG Xin;YUAN Huacheng;LIU Fuzhou;ZHANG Jingsheng(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《固体火箭技术》2022年第4期522-531,共10页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(11772155);航空基金(20200012052001)。

摘　　要：为实现高超声速进气道快速设计、缩短设计迭代周期,将基于激波形状和基于壁面参数分布的型面逆设计方法相结合,给出了一种兼顾几何约束和气动需求的曲面压缩高超声速进气道参数化设计方法;同时,基于有旋特征线法提出了一种进气道流场快速求解方法(MOC),通过准确捕捉弯曲激波、唇罩激波、肩部膨胀区以及反射激波系等流场结构,实现了对高超声速进气道设计工况及亚额定工况下流场及无粘性能的快速求解。与CFD方法相比,MOC方法求解效率提升300倍左右,不同工况下的进气道喉道截面性能求解误差不超过2%;将高超声速进气道参数化设计方法与流场快速求解方法相结合,在获取进气道设计方案的同时,可快速获取进气道在不同工况下的无粘气动性能,从而为进气道的自动优化设计提供支撑。In order to realize rapid design of hypersonic inlet and shorten the design iteration period,a parameterized design method of curved compression hypersonic inlet was presented by integrating the inverse design method based on shock profile and wall parameter distribution law,which can take into account geometric constraints and inlet aerodynamic performance.At the same time,a rapid solution method(MOC)of inlet flow field was proposed based on the rotating characteristic method.By accurately capturing the flow field structures such as curved shock wave,lip cowl shock wave,shoulder expansion zone and reflected shock wave system,the flow field and inviscid performance of hypersonic inlet under design conditions and sub-standard conditions can be rapidly solved.Compared with CFD method,the efficiency of MOC method in this paper is improved by about 300 times,and the solution error of inlet throat section performance under different operating conditions is less than 2%.By combining the parameterized design method of hypersonic inlet with the rapid solution method of inlet flow field,the inviscid aerodynamic performance of the inlet under different operating conditions can be quickly obtained while obtaining the design scheme of the inlet,so as to provide support for the automatic optimization design of the inlet.

关 键 词：高超声速进气道 有旋特征线法 气动设计 流场求解 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]