高超声速二维前体/进气道一体化优化设计研究

Integrative Optimum Design and Research for Hypersonic Two Dimensional Forebody/Inlet

本文以二维高超声速进气道的最大总压恢复系数为主要设计指标,同时兼顾进气道的升力和阻力。通过理论分析和数值计算给出了二维高超声速飞行器前体、进气道唇口以及进气道内部的优化设计方法,并同时与等激波强度三楔角压缩的前体设计以及平直唇口设计相比较,说明其优越性。最后计算结果表明:高马赫条件下,单楔角加等熵压缩的前体性能优于等激波强度三楔角压缩的前体性能;进气道唇口采用长楔角性能优于直底板唇口;隔离段与水平方向夹一个小角度是很有利的。

By theoretic analysis and numerical calculation , an optimum design method for hypersonic two dimensional forebody, cowl and inner of the inlet is figured out based on the highest total pressure recovery and considering the lift force and the drag force. In oilier to demonstrate the advantages, the design is compared with the three wedge external compression of equal shock wave intensity and the plane cowl. The calculations indicate that in hypersonic flow, the performance of one wedge and isentropic compression is much better than that of three wedge external compression of equal shock wave intensity and the cowl that adopts a long wedge is much better than the plane one. It also has advantages for the isolator to be tilted in smaller intersection angle with the horizon.