高超声速二元进气道前体曲线激波逆向设计  

Inverse Design of the Fore-body Curved Shock Wave of the Hypersonic Planar Inlet

作　　者：郭善广[1] 王振国[1] 赵玉新[1] 范晓樯[1] 

机构地区：[1]国防科学技术大学高超声速冲压发动机技术重点实验室,湖南长沙410073

出　　处：《航空学报》2014年第5期1246-1256,共11页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(11072264)~~

摘　　要：为实现高超声速二元进气道前体激波的压缩能力、压缩效率、流量捕获特性和结构长度可控,提出了平面曲线激波逆向设计方法。采用B-Spline曲线控制激波形状。利用有旋特征线法,求解激波的影响域及决定激波的壁面。设计了一凹激波,并对波后流场进行CFD无黏数值模拟,CFD结果和设计结果一致,验证了设计方法的可行性。此外,还设计了直激波、凹激波和凸激波3种激波,并对其在设计点和非设计点处的性能开展了数值研究。在设计点处,分析了激波的压缩比、激波的总压恢复系数、激波压缩区的压升、激波压缩区出口马赫数和流动角随激波控制角的变化规律。在非设计点处,分析了激波压缩区的流量系数和总压恢复系数随攻角和马赫数的变化规律。To achieve the compression capacity,compression efficiency,flow mass capture capacity,and geometric length of the hypersonic planar inlet controllable,a design method of the planar curved shock wave is proposed.The shock curve is specified with the B-Spline function in advance,and the domain of influence of the shock wave and the wall profile are solved by the rotational method of characteristics.With the inviscid CFD simulation of the concave shock wave,the present design method is validated.Three types of shock wave,including straight,concave and convex shock waves,are designed,and their performances are investigated.At on-design point,the variations of contraction ratio,total pressure recovery coefficient,pressure rise,and exit Mach number and flow angle with the governing angle of shock wave are illustrated.In addition,at off-design point,the variations of the total pressure recovery coefficient and flow mass coefficient with the angle of attack and Mach number are shown.

关 键 词：高超声速进气道 激波 逆向方法 特征线法 性能分析 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]