高超声速升力前体构型设计与数值分析

Numerical Analysis of Configuration Design of Hypersonic Lift Forebody

采用楔形角方法设计生成了一种小型高超声速巡航飞行器升力前体构型,利用带惩罚函数的单纯形法对得到的升力前体进行了优化设计,通过数值模拟方法研究了优化设计后的升力前体气动特性。结果表明:楔形角方法是一种生成高超声速飞行器升力前体的高效方法;升力前体在不同飞行马赫数下上下表面存在压力沟通,将导致前体预压缩面在展向存在横向流动,造成进气道进口流场不均匀;采用在升力体两侧增加侧缘的方法可有效减小前体预压缩面横向流动,提高前体升力。

The lift forebody configuration of a small hypersonic vehicle was designed by using the wedge angle method. The lift forebody created has been optimized by the simplex method with a penalty function.The aerodynamic characteristics of the forebody optimized were investigated by numerical method. The research results show that the wedge angle method is a high efficient way to generate the lift forebody of the hypersonic vehicle; On the design mach number,there is pressure leaking between the upper and lower surface of lift forebody,which leads to lateral flow in the spanwise on the precompression plane and creates the unhomogeneity of inlet flow field; Adding side skirts on the both sides,which can reduce the lateral flow on the forebody＇s precompression plane and raise the forebody lift.