Numerical and Experimental Investigations on Mach 2 and 4 Pseudo-Shock Waves in a Square Duct
Numerical and Experimental Investigations on Mach 2 and 4 Pseudo-Shock Waves in a Square Duct
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DOI：
10.2322/tjsass.47.124
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发表时间：
2004-08
影响因子：
1.1
通讯作者：
Liqun Sun;H. Sugiyama;Kazuhide Mizobata;Ryojiro Minato;A. Tojo
中科院分区：
文献类型：
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作者：
Liqun Sun;H. Sugiyama;Kazuhide Mizobata;Ryojiro Minato;A. Tojo
分别通过2马赫和4马赫的数值模拟和实验，研究了方形风管中λ型和x型伪激波的结构和特性。实验在压力-真空超音速风洞中进行，实验横截面为80×80 mm2。采用Harten-Yee二阶TVD格式和Baldwin-Lomax湍流模型进行了数值模拟。2马赫和4马赫的雷诺数分别为Re∞=2.53×107和Re∞=2.36×107，两种情况下的流动约束均为δ∞⁄h=0.35。计算结果与实验结果吻合较好。在此基础上，采用数值模拟的方法对实验难以得到的流量进行了分析。虽然在马赫数为4的情况下，由于实验中的不对称特性无法在数值模拟中再现，计算结果与实验结果存在一些差异，但计算结果对于理解这一复杂的不对称现象具有一定的价值。
The structures and characteristics of λ-shaped and X-shaped pseudo-shocks in a square duct are investigated through numerical simulations and experiments at Mach 2 and Mach 4, respectively. The experiments were carried out in a pressure-vacuum supersonic wind tunnel with a test cross section of 80×80 mm2. Numerical simulations were carried out using the Harten-Yee second-order TVD scheme and the Baldwin-Lomax turbulence model. The Reynolds numbers for the Mach 2 and 4 cases were Re∞=2.53×107 and Re∞=2.36×107, respectively, and the flow confinement was δ∞⁄h=0.35 for both cases. The computational results for the Mach 2 pseudo-shock wave are in good agreement with the experimental results. Based on this agreement, the flow quantities, which are very difficult to obtain experimentally, were analyzed by numerical simulation. Although several differences were found between the computational results and experiments in the case of Mach 4 due to asymmetric characteristics in experiment which could not be reproduced in numerical simulation, the computational results are valuable for understanding this complex asymmetric phenomenon.