超声速变马赫数风洞流场参数线性变化验证

旋转喷管型面使超声速变马赫数风洞在单次运行过程中可连续调节实验区的马赫数，便于研究飞行器的机动过程、进气道起动过程中的气动问题。在控制喷管型面旋转过程中，流场参数能否线性变化是衡量超声速变马赫数风洞性能的一个重要指标。分析变马赫数风洞实验区流场参数的线性变化规律，利用弹簧光顺的动网格技术建立数值仿真模型，验证喷管位于马赫数3.041~3.215 范围所对应的位置时，实验区流场参数是否满足线性变化规律。结果表明：通过对喷管型面旋转的控制实现了风洞实验区流场参数的线性变化，动态计算结果与预期实验区流场参数线性变化规律吻合良好；在不同加速度的流场参数线性变化过程中，各时刻实验区的平均参数与预期参数之间的偏差均小于0.13%。

Linear Change Verification of Flow Field Parameters in Supersonic Continuously Variable Mach Number Wind Tunnel

Rotating nozzle profile enables the supersonic variable Mach number wind tunnel to continuously adjust the Mach number of the experimental area during a single operation, which is important for studying the aerodynamic problems in the maneuvering process of the aircraft and the starting process of the inlet. In the process of controlling the nozzle profile rotation, whether the flow field parameters can change linearly is an important criterion to measure the performance of supersonic variable Mach number wind tunnel. Therefore, this paper analyzes the linear variation law of flow field parameters in the experimental area of variable Mach number wind tunnel, and a numerical simulation model is established using the spring smoothing dynamic grid technique to verify whether the flow field parameters in the experimental area meet the linear variation law when the nozzle is located at the corresponding position of Mach number 3.041~3.215. The results show that the linear change of the flow field parameters in the wind tunnel experimental area is achieved by controlling the rotation of the nozzle profile, and the dynamic calculation results are in good agreement with the expected linear change law of the flow field parameters in the experimental area. In the linear change process of flow field parameters with different accelerations, the deviation between the average parameters of the experimental area and the expected parameters at each time is less than 0.13%.