中文摘要：

为了探究前体典型几何参数对高超声速前体／进气道气动特性的影响，在相同的前体外压缩角度和几何长度下，对基于圆锥截线参数控制横向截面的高超声速前体流动特性开展了三维数值模拟分析。采用控制变量法研究了高超声速前体宽度比、形状参数、形状角度参数以及水平半宽控制曲线次数对高超声速前体／进气道气动性能的影响。结果显示：上述四个几何参数对前体横向压力梯度的构建均产生一定的影响，导致前体横向溢流，进而影响前体／进气道的气动性能。增大前体宽度比、形状参数、水平半宽控制线次数，减小形状角度参数，可减小前体展向压力梯度及横向溢流，提高前体／进气道流量捕获特性，在本文研究范围内，上述参数变化对应的前体，进气道流量系数分别增加了25．1％，13．7％．20．3％72．12．2％。

英文摘要：

In order to investigate the effects of different configuration of hypersonic forebody on the perfor- mance of inlet, the hypersonic forebody was designed based on conic section under the same external compres- sion angles and compression ramp length conditions and analyzed through three dimension numerical simulation. The effects of four hypersonic forebody cross section parameters including width ratio, shape parameter, angle parameter and order of horizontal half width control curve were analyzed. The numerical simulation results indicat- ed that these four parameters affected the performance of the inlet according to the influence of the lateral pres- sure gradient along the forebody. The increase of the width ratio, shape parameter and order of horizontal half width control curve and decrease of angle parameter would reduce the lateral pressure gradient and lateral over- flow and increase the mass flow ratio of the inlet. In this paper, the change of these four parameters improved the inlet mass flow ratio by 25.1%, 13.7%, 20.3% and 12.2%, respectively.