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针对超燃冲压发动机进气道由于激波-边界层干扰引起的边界层分离以及进气道堵塞问题,提出了一种基于Tollmien-Schlichting(T-S)波谐频共振原理的进气道边界层控制方法,并通过一种典型的二元进气道风洞试验进行了方法验证.研究结果表明,提出的转捩控制方法能够较好地消除由激波-边界层干扰而引起的边界层分离现象,进而降低边界层分离对进气道性能的不良影响,确保进气道性能.同时说明,在超燃进气道设计过程中,需要充分考虑边界层转捩问题,引入有效的边界层转捩控制方法,以保证发动机的正常工作.
Aiming at the boundary layer separation and inlet blockage caused by shock-boundary layer interference in the intake of scramjet engine, a boundary layer control of intake duct based on the Tollmien-Schlichting (TS) harmonic resonance principle is proposed Method and verified by a typical binary inlet wind tunnel test.The results show that the proposed method can effectively eliminate the boundary layer separation caused by the shock wave-boundary layer interference , So as to reduce the negative influence of the boundary layer separation on the performance of the air intake and ensure the performance of the air intake.At the same time, it is necessary to fully consider the boundary layer transition in the design process of the fuel inlet and to introduce effective boundary layer transition Control methods to ensure the normal operation of the engine.