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针对一种起动马赫数Ma=2.0、设计马赫数Ma=3.0的超声速进气道,首先结合等激波强度和数值模拟的方法,分析了进气道各几何参数间的相互制约关系并设计了一种性能较优的传统构型。在此基础上,分析了不同边界层吸除装置对进气道性能的影响。结果表明,恰当的选择吸除装置和吸除流量,可明显增强进气道能够承受的最大反压并改善进气道在起动马赫数和设计马赫数下的总压恢复系数。探索了吸除装置合理的设计方法,可为工程设计提供一定的理论支撑。
Aimed at a supersonic inlet with a Mach number of Ma = 2.0 and a Mach number of Ma = 3.0, the geometrical parameters of the inlet were analyzed in terms of iso-shock intensity and numerical simulation. A better performance of the traditional configuration. Based on this, the influence of suction devices with different boundary layers on the performance of air intake is analyzed. The results show that the proper choice of suction and suction flow rate can significantly enhance the maximum backpressure that the air intake can withstand and improve the total pressure recovery coefficient of intake port at starting Mach number and design Mach number. Explored the rational design of suction device, which can provide some theoretical support for engineering design.