高超声速进气道低马赫数不起动和再起动试验

doi:10.7527/S1000-6983.2017.121146

Abstract

Abstract:

To enrich the understanding of the mechanism for hypersonic inlet unstart,a wind tunnel test is conducted to investigate the low Mach number unstart and restart of a truncated two-dimensional hypersonic inlet. By varying the inlet angle of attack and the downstream choking degree, the variation of the inlet flow Mach number and heat release of combustion in real flight conditions are simulated in this test. The high-speed Schlieren imaging technology and time-resolved pressure measurements are used to record the instantaneous flow pattern and surface pressure signals. The results show that during the unstart process at low Mach number, the separation bubble induced oblique shock is influenced by the oscillation characteristic of the separation bubble, and oscillates slightly around the cowl lip to introduce a type of small-amplitude disturbance without base frequency. This disturbance gradually disappears with the increase of the Mach number and restart of the inlet. Hysteresis of swallow of separation bubble is also observed in the test. When the inlet recoveries from the little buzzle state to the start state, the separation bubble cannot be fully swallowed due to the presence of high pressure downstream during the restart process, and exhibits as a small-amplitude oscillation similar to the one in low Mach number unstart process. The oscillation does not disappear until the inlet exit is fully open and the separation bubble in the entrance is swallowed simultaneously, and then the inlet returns to start successfully.

Key words: hypersonic inlet, low Mach number, unstart, restart, hysteresis

CLC Number:

V211.3

WANG Chenxi, TAN Huijun, ZHANG Qifan, SUN Shu. Test of low Mach number unstart and restart processes of hypersonic inlet[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(11): 121146-121146.

References

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Test of low Mach number unstart and restart processes of hypersonic inlet

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