连续伴随方法在二维高超声速进气道优化中的应用  

Applications of continuous adjoint method in 2D hypersonic inlet optimization

作　　者：高昌[1] 张小庆[1] 贺元元[1] 吴颖川[1] 乐嘉陵[1] GAO Chang;ZHANG Xiaoqing;HE Yuanyuan;WU Yingchuan;LE Jialing(Science and Technologyon Scramjet Laboratory,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China)

机构地区：[1]中国空气动力研究与发展中心高超声速冲压发动机技术重点实验室

出　　处：《空气动力学学报》2020年第1期21-26,共6页Acta Aerodynamica Sinica

摘　　要：针对连续伴随方法,开展在二维高超声速进气道优化中的应用研究。进气道构型采用基于特征线法设计的曲面压缩进气道,运用自由曲面变形FFD方法对进气道外压缩面参数化控制,在黏性情况下基于连续伴随方法以进气道流量为目标开展优化研究。采用三套网格研究外压缩面壁面灵敏度的影响因素,结果表明壁面灵敏度对边界层网格依赖性较强;通过有限差分法对连续伴随方法得到的目标函数梯度进行验证。基于以上方法和结论,采用拟牛顿BFGS方法以进气道流量为目标函数对外压缩面优化,优化后唇口处入射激波实现封口,外压缩面最大法向位移为5.6mm,进气道流量提高6.3%,整体性能得到提升。优化结果表明,伴随方法可有效应用于高超声速进气道优化。The application of the continuous adjoint method has been conducted on a 2 D hypersonic inlet design optimization.The 2 Dhypersonic inlet is an inviscid curved compression configuration designed based on characteristics method.The external compression surface has been parameterized through the free form deformation(FFD)method.The viscous mass flow rate of the inlet has been taken as the optimization objective.The flow governing equations and the continuous adjoint equations have been solved on three different grids to analyze the external compression surface sensitivity contrastively.The results indicate that the external compression surface sensitivity has a strong boundary layer mesh dependence.The objective gradients obtained by the continuous adjoint method are credible according to the comparison with the finite difference method.The BFGS algorithm has been adopted,and the optimization results show that the incident shock wave seals the external flow at the cowl.This behavior increases the inlet mass flow rate by 6.3%,and the integrated performances of the inlet have been promoted.The maximum normal displacement of the external compression surface is 5.6 mm.Based on the optimal results,the adjoint method could be applied successfully in hypersonic inlet design optimizations.

关 键 词：连续伴随方法 高超声速进气道 构型优化 

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]