摘要
以压力梯度可控设计方法优化后的二维曲激波基准流场为基础,结合流线追踪和截面渐变技术实现了矩形进口、圆形进口以及方转椭圆进气道设计,证明基于二维曲激波基准流场可以设计出各种进出口截面形状的高超声速进气道.利用上述设计方法设计的3种不同进出口形状的高超声速进气道,与相同约束条件下的常规二元三楔进气道进行了对比.数值仿真研究表明:3种非常规进气道设计点无黏流场马赫数分布及总体性能与基准流场接近,具有二维基准流场的特征,波系结构简单,出口畸变较小.此类进气道的总体性能相当,较常规进气道可以显著缩短外压段长度,流量捕获能力更强,非设计点也表现出良好的性能.以上结果表明该设计方法是可行的,值得进一步研究.
The rectangular and circular shape intake hypersonic inlets and rectangular to elliptical shape transition hypersonic inlet have been designed with the technologies of streamline tracing and varying section using an optimized two-dimensional（2-D） curved surface basic flowfield with controlled pressure gradient.It proved that hypersonic inlets with various entrance and exit shapes can be designed based on 2-D curved surface basic flowfield.Utilizing this design method,three hypersonic inlets with different entrance and exit shapes have been generated and compared with typical 2-D inlets under the same constraints.The numerical simulation shows that Mach number distributions and general performance for unconventional inlets approximate the basic flowfield at design point under the inviscid condition,which has the characteristics of 2-D basic flowfield that shock structure is simple and exit distortion is low.This kind of inlet has the roughly equivalent general performance.Comparison with typical 2-D inlet indicates that they significantly reduce the length of external compression portion,have greater flow ability to capture and demonstrate better performance at off design points.In conclusion,this design method is feasible and is worth being investigated further.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2012年第9期2004-2012,共9页
Journal of Aerospace Power
基金
国家自然科学基金(90916029)
关键词
高超声速进气道
基准流场
弯曲激波
流线追踪
数值仿真
hypersonic inlet； basic flowfield； curved shock； streamline tracing； numerical simulation
