中文摘要：

不同的二元进气道前缘激波压缩方式直接影响进气道性能参数，尤其是流量系数。详细分析研究了两种类型的高超二元曲面压缩进气道前缘激波随攻角和来流马赫数变化的特性。计算结果显示，对于初始楔加等熵压缩的二元曲面进气道，在给定的初始楔角下，随着进气道攻角的增大前缘激波与压缩面之间的夹角先减小后增大，随着来流马赫数的增大，前缘激波与压缩面之间的夹角减小；而对于等压力梯度分布控制的弯曲激波压缩二元曲面进气道，随着进气道攻角或来流马赫数的增加，前缘激波与压缩面间的夹角都增大。通过理论和计算分析表明，是斜激波与马赫波不同的相交模式造成了两种曲面压缩进气道的前缘激波随进气道攻角和来流马赫数变化的特性不同。

英文摘要：

Different leading edge shock on hypersonic curved ramp two-dimensional inlet directly influ- ences the inlet performance, specially, the flow coefficient. A detailed analysis and investigation was per- formed on the variation characteristics of leading edge shock generated by two different inlets response to the variation of inlet attack angle and inflow Mach number. The calculation results reveal that for wedge-isen- tropic two-dimensional inlet, the angle between the leading edge shock and compression surfaces decreases in advance, then increases with increase of the inlet attack angle. However, the angle always decreases with the increase of the free stream Mach number, whereas, for two-dimensional hypersonic curved shock com- pression inlet with the law of constant pressure gradient, the angle between the leading edge shock and com- pression surfaces decreases with increase of both the attack angle and the free stream Mach number. Ac- cording to theory and calculation analysis, different oblique shock and Mach wave interaction mode causes different characters of leading edge shock generated by two different inlets response to the variation of inlet attack angle and inflow Mach number.