高超声速进气道快速破膜开启的流动特性

doi:10.7527/S1000-6893.2014.0303

Abstract

Abstract:

Reliable in-flight starting of the hypersonic inlet is of critical importance for the successful operation of scramjet engines and taking the method of diaphragm rupture can effectively improve the inlet starting ability due to unsteady flow effect. In this paper, time-accurate computations have been performed to investigate the effects on inlet starting process at different diaphragm positions. The evolution process of the inlet flow pattern is analyzed and the mechanism of the separation bubble formation in the throat is thus elucidated. The results show that the unsteady reflected shock interacts with the interface and expansion waves to trigger a low-speed flow when no separation bubble occurs in front of the diaphragm. A separation bubble then forms in the inlet throat, resulting from the low-speed flow under the interaction of cowl shock. Installing the diaphragm downstream would improve the inlet starting ability by decreasing the low-speed flow area. When large separation bubble occurs in front of the diaphragm, the separation bubble will first evolve to a low-speed flow after diaphragm rupture then develop to a new separation in the throat. The inlet starting ability degrades significantly.

Key words: hypersonic inlet, diaphragm rupture, unsteady flow effect, shock wave/boundary layer interaction, separation flow

CLC Number:

V214.8

XU Xiao, YUE Lianjie, LU Hongbo, XIAO Yabin, ZHANG Xinyu. Flow characteristics of hypersonic inlet starting with diaphragm rupture[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(6): 1795-1804.

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Flow characteristics of hypersonic inlet starting with diaphragm rupture

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