一种改善高超声速进气道自起动能力的流场控制研究

doi:10.7527/S1000-6893.2014.0125

Abstract

Abstract:

To improve the self-start performance of hypersonic inlet at low Mach number, a flow-control conception of backflow duct is put forward, which is driven by the pressure difference generated by the separation induced shock under unstart conditions. The influencing principles are analyzed, and the characteristics of inlet's flow field and the inlet's aerodynamic performances affected by variable geometry parameters of the backflow duct are investigated. Finally, compared with the primary inlet's performances, the results indicate that due to the backflow duct, the self-start Mach number is ascended from Ma=4.7 to Ma=3.6, expending the operating Mach range remarkably. The location of the backflow duct's entrance influences the self-start performance significantly, while the location of backflow duct's exit and the width of backflow duct's section (b≥8 mm)scarcely affectes the self-start ability. At low Mach number, the unstarted flow field of inlet is improved by the backflow duct considerably.But at high Mach number, the influence of backflow duct would be slight, satisfying the design performance requirements.

Key words: hypersonic inlet, backflow duct, geometry parameters, self-start Mach number, inlet performances

CLC Number:

V231.3

WANG Jianyong, XIE Lyurong, ZHAO Hao, TENG Yulin. A flow-control conception of improving self-start performance of hypersonic inlet[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(5): 1401-1410.

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A flow-control conception of improving self-start performance of hypersonic inlet

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