飞行器级间段跨声速脉动压力特性试验

doi:10.7527/S1000-6893.2019.22815

Abstract

Abstract: Variations of fluctuating pressure on different interstage sections at transonic speeds between Ma at 0.75 to 1.2 are investigated through wind tunnel measurement, and the effect laws of the pressure fluctuation on the flight vehicle with different cone angles and lengths are obtained. Results show that the strong fluctuating pressure is mainly caused by low-frequency shock wave oscillation, of which the power is largely located in the range of 100 Hz. Meanwhile, with the increase of Mach number, the maximum fluctuating pressure coefficient in shoulder region increases first and then decreases sharply for each configuration, and the peak value of the fluctuating pressure coefficient moves backward along the flow direction. Moreover, by comparing the maximum fluctuating pressure coefficient of five cone angle configurations, including 10°, 12.7°, 15.3°, 20°, and 25°, this paper finds that with the increase of cone angle, the pressure fluctuation increases gently when the cone angle is less than 15°, and the value increases sharply as the cone angle increases more. Furthermore, the comparison of different cone length configurations shows that while the cone length is of almost no effect on the peak value of the local fluctuating pressure, it impacts on the scale and range of Mach number at peak value. The longer the conical connector, the larger the effect area, and the wider the range of Mach number in which the peak of pressure fluctuation arises.

Key words: flight vehicle, interstage section, cone angle, cone length, fluctuating pressure, wind tunnel test

CLC Number:

V19
O354.2

WU Lilong, CAO Xiaolong, WANG Jing, ZHOU Danjie, LUO Jinling. Pressure fluctuation laws test on interstage section of flight vehicle at transonic speeds[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(8): 122815-122815.

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Pressure fluctuation laws test on interstage section of flight vehicle at transonic speeds

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