马赫数4二维直管内拟似冲击波实验和数值研究

 通过计算流体力学数值仿真和高速彩色纹影照片显示技术对马赫数4拟似冲击波进行研究。实验是在日本室兰工业大学的压力—真空型超声速风洞中进行的。数值计算是采用三阶精度的QUICK格式和Spalart-Allmaras湍流模型进行的。用实验验证CFD模型,计算结果与实验显示出较好的一致性。可以得出结论,从目前的CFD模型获得的计算结果是精确的。因而,实验很难获得的拟似冲击波流场内部一些流动量可以通过数值仿真结果进行分析。另外,推测了马赫数4拟似冲击波非对称的原因。

Numerical and Experimental Investigations of Mach 4 Pseudo-Shock Waves in a Two-dimensional Square Duct

Mach 4 Pseudo Shock Wave (PSW) in a two-dimensional square duct is researched through computational fluid dynamics (CFD) numerical simulation and high-speed color schlieren photography visualization techniques. The experiment was done in the pressure-vacuum supersonic wind tunnel of Muroran Institute of Technology of Japan. The numerical simulation is carried out with the third-order accurate QUICK scheme and Spalart-Allmaras turbulence equation. Experiment is used to validate the CFD model. The computational results show agreement with the experimental results. It can be concluded that the numerical flow visualizations obtained from the present CFD model are accurate. Therefore, the flow quantities, which are very difficult to be obtained experimentally, can be analyzed by numerical simulation. Moreover, the reason that Mach 4 oblique shock wave is asymmetric is conjectured.