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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。
Different binary inlet shock suppression methods directly affect the inlet performance parameters, especially the flow coefficient. The characteristics of two types of hyperbolic curved inlet front shock wave along with attack angle and Mach Mach number are analyzed in detail. The results show that for the initial wedge plus isentropic compression of the binary surface inlet, with the initial initial wedge angle, with the angle of attack of the inlet increases, the angle between the front shock and the compression surface First reduce and then increase, with the Mach number increasing, the angle between the leading edge shock and the compression surface decreases; while the pressure gradient distribution control of the curved shock compression Binary Surface Inlet With the increase of the angle of attack or Mach Mach number, the angle between the front shock and the compression surface increases. The theoretical and computational analysis shows that the different intersecting modes of oblique shock and Mach wave cause different characteristics of the front shock of the two curved inlet ports with the changes of the angle of attack of the inlet port and Mach Mach number.