高超声速二元弯曲激波压缩面反设计方法的参数化研究  

Parameter Analysis of Reverse Design Method of 2-D Hypersonic Curved Shock Compression Surface

作　　者：王磊[1] 张堃元[1] 向有志[1] 南向军[1] 苏纬仪[1] 

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：《南京航空航天大学学报》2013年第4期441-446,共6页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家自然科学基金重大研究计划重点支持(90916029)资助项目

摘　　要：基于压力分布反设计高超声速进气道弯曲压缩面的方法,采用数值模拟按照正交设计原则,研究了壁面压力分布函数中各设计参数对激波长度比、出口压比、总压恢复系数、出口总压畸变和压缩面阻力系数等压缩性能的影响规律。结果表明:反设计方法可准确设计出满足指定压力分布的弯曲压缩面;设计参数中压缩面中段压力梯度的大小(G2和G3)对压缩性能的影响最为显著。ABased on the reverse design method of hypersonic inlet curved compression surface from the as signed pressure distribution, the effect of design parameters on the compression performance such as shock length ratio, pressure ratio, totalpressure recovery, distortion and drag coefficient is investiga ted, using numerical simulation according orthogonal design. The results show that, curved compres sion surface designed with this method can exactly meet the expected pressure distribution, and the pressure gradient G2 and G3 on the middle section of the curve have remarkable influence on compression performance.

关 键 词：高超声速进气道 弯曲激波压缩 曲面压缩 反设计 敏感度分析 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]