超燃冲压发动机进气道低马赫数起动性能研究

摘要

The starting of hypersonic inlet is a common question at low Mach number condition. In this paper a 2-D scramjet mixed-compression inlet is designed by the method of constant shock intensity, the inlet configuration is present. The inlet flow field and performance at design and off-design points are simulated by numerical approach, the start characteristics at low Mach number was investigated. It shows that, the additional drag of the designed inlet is low and the total-pressure recovery coefficient is high; at the low Mach number, the start requirement can be satisfied by adding the boundary layer suction installation; the inlet starting characteristics is sensitive to suction location, the suction position upstream of recirculation zone is of the most effectiveness.%为探讨高超声速进气道在低马赫数普遍存在的起动问题，采用等激波强度法设计了超燃冲压发动机二维混压式前体／进气道，给出了前体／进气道的几何尺寸，对所设计的进气道在设计状态、非设计状态的性能与流场进行了数值模拟，对低马赫数下进气道的起动问题进行了研究。研究表明：设计的进气道附加阻力较小，总压恢复系数较高，在低马赫数下通过附面层抽吸可以满足起动要求，抽吸位置对进气道的起动性能影响很大，靠近回流区前侧抽吸最具有效果。