针对火箭橇气流通道装置开展设计与数值模拟研究。首先,将气流扩张通道内部划分为初始源流膨胀区、消波区和均匀流试验区,然后,应用Foelsch方法对初始膨胀段型线进行设计,采用基于轴线马赫数预设的特征线方法对过渡消波段进行设计,最后,针对扩张比为2.5的火箭橇气流扩张装置,在运行速度为1.5Ma、2Ma、2.5Ma和3Ma条件下开展数值模拟分析,结果表明,通道进口膨胀波随着运行速度的增加而减弱,1.5Ma速度条件下的相对压力峰值为0.14 MPa,3Ma速度条件的相对压力峰值为0.018 MPa,相对压力峰值下降约87%,使进口条件得到改善,最大马赫数模拟偏差为3.9%,静压模拟偏差为6.5%。

The application of airflow expansion channel device in rocket sled test can obtain higher airflow velocity at the exit, so as to realize the simulation of hypersonic environment. The design and numerical simulation of airflow channel device for rocket sled are studied. Firstly, the internal part of the air expansion channel is divided into initial source flow expansion area, wave attenuation area and uniform flow test area. Foelsch method is used to design the initial expansion section profile, and the characteristic method based on the preset Mach number of the axis is used to design the transition wave attenuation band. On this basis, numerical simulation analysis is carried out for the rocket sled air expander with a growth rate of 2.5 at the operating speeds of 1.5Ma, 2Ma, 2.5Ma and 3Ma. The results showed that the expansion wave at the inlet of the channel weakened with the increase of the operating speed. The peak relative pressure at 1.5Ma is 0.14MPa, and the peak relative pressure at 3Ma is 0.018 MPa. The decrease of relative pressure is about 87% and the inlet condition is improved. After data comparison,the maximum mach number simulation deviation is 3.9%, and the static pressure simulation deviation is 6.5%.