飞行器级间段跨声速脉动压力特性试验

通过脉动压力风洞试验测量，对比分析了跨声速（马赫数介于0.75~1.2）不同锥角和锥长大小的级间段对锥柱外形飞行器局部脉动压力的影响规律。结果表明，肩部脉动压力主要由以低频为主导的激波振荡所致，能量集中在100 Hz左右的窄带区间，且表现为随着马赫数增加，脉动压力系数峰值先增大后减小，并随着肩部激波的后移而不断向后推移。此外，通过对比分析5种不同锥角模型（10°、12.7°、15.3°、20°、25°）的脉动压力系数最大值发现，随着锥角的增加，脉动压力表现出当锥角小于15°时先平缓增加，随着锥角增大脉动压力系数增加幅度进一步加大的趋势。对比分析不同锥长模型的结果发现，锥长对局部脉动压力的最大峰值几乎没有影响，影响的只是脉动压力在肩部作用区域的大小以及峰值出现的马赫数范围，且表现为锥柱级间段越长其作用范围越大，对应于峰值的马赫数区间越宽。

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

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.