“咽”式高超进气道流动特性及性能分析

采用数值模拟的方法比较分析了一种矩形型面的内收缩进气道和一种椭圆型面的"咽"式进气道的流动特性和性能.这两种内收缩进气道都足以四道平面斜激波三维流场为基本流场,利用流线追踪技术得到的.研究结果表明,该"咽"式进气道对设计状态下的攻角变化不太敏感;在非设计状态下具有较高的流量捕获和压缩能力;另外,由于其浸湿面积小,进气道内附面层增长缓慢,激波与附面层干扰较弱.因此,这种"咽"式流道可作为吸气式高超声速飞行器进气道的一个有利选择方案.

Investigation of flow characteristic and performance on the "Jaws" hypersonic inlet

Two different inward turning inlets,i.e.a classic rectangular cross-section and a "Jaws" one,were explored numerically.Based on a three dimensional flowfield with four planar shock waves,these two were derived with the technology of streamtracing.Results indicate: the performance of the "Jaws" inward inlet is insensitive to the angles of attack on design point;the inlet has high mass capture and compression capability on off-design point;in addition,boundary-layer growth of the inlet develops slowly and shock/boundary-layer interaction is weak because of the diminished wetted area.In conclusion,this "Jaws" inward inlet is an advantageous option of the hypersonic inlet.