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针对轴对称基准流场中前缘曲激波靠近中心体的部分激波强度过大现象,基于马赫数分布可控反设计方法,将这道前缘曲激波分解为一道较弱弯曲激波和部分等熵压缩波,改进的基准流场存在“四波四区”结构且压缩效率明显提高.基于该改进的基准流场和常规“两波三区”基准流场分别设计了圆形进口的内收缩进气道并对其流场特点和性能进行数值研究.结果表明:改进的进气道的流场能较好保持基准流场的特点;在来流马赫数为4.0~7.0范围内具有较高的压缩效率和良好的流量捕获能力,设计点的出口压比和总压恢复系数分别为17.56和0.540;改进的进气道采用来流马赫数从高到低前缘弯曲激波和汇集的等熵压缩波依次封口的设计概念,在提高流量捕获能力的同时减小了总压损失,总体性能优于常规进气道,来流马赫数为7.0时总压恢复系数相对提高了23.6%,来流马赫数为4.0时流量系数相对提高了5.7%.
Aiming at the phenomenon of excessive partial shock intensity of the frontal quasar near the central body in an axisymmetric reference flow field, this front-edge quincunrodal wave is decomposed into a weak bending shock wave based on a controllable anti-Mach-design method And some isentropic compressional waves, the improved reference flow field has a “four-wave four-zone” structure and the compression efficiency is obviously improved. Based on the improved reference flow field and the conventional “two-wave three-zone” reference flow field, The results show that the improved inlet flow field can better maintain the characteristics of the reference flow field. When the incoming Mach number is 4.0 ~ 7.0 range with high compression efficiency and good flow capture capacity, the design point of the outlet pressure ratio and the total pressure recovery coefficient of 17.56 and 0.540, respectively; improved inlet using the flow Mach number from high to low front Bending shock wave and pooled isentropic compression wave sealing design concept in order to improve the flow capture ability while reducing the total pressure loss, the overall performance is better than the conventional inlet, the flow Mach number is 7.0 when the total pressure recovery factor A relative increase of 23.6% and a Mach-rate of 4.0 When the flow coefficient increased by 5.7%.