Large-Eddy Simulations of Perfectly Expanded Supersonic Jets Using an Unstructured Solver
Large-Eddy Simulations of Perfectly Expanded Supersonic Jets Using an Unstructured Solver
复制标题
使用非结构化求解器对完美展开的超音速喷气机进行大涡模拟
DOI：
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发表时间：
2012
期刊：
影响因子：
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通讯作者：
P. Moin
中科院分区：
文献类型：
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作者：
S. Mendez;M. Shoeybi;Arjun Sharma;F. Ham;S. Lele;P. Moin
对超声速射流进行了大涡模拟，以验证二阶有限体积非结构求解器在航空声学应用中的有效性。计算了两股从轴对称喷管中喷出的马赫数为1.4的超音速射流：一股雷诺数为150，000的未加热射流和一股雷诺数为76，000、温度比为1.75的加热射流。流场和噪声计算结果与美国宇航局格伦研究中心的实验数据进行了比较。计算结果表明，非结构化求解器的计算结果与实验数据吻合较好，包括时均量和脉动量、射流速度谱以及采用Ffowcs-Williams和Hawkings方程积分得到的近场和远场声场。
Large-eddy simulations of supersonic jets are performed to validate the development of a second-order finite volume unstructured solver for aeroacoustic applications. Two supersonic jets issuing from an axisymmetric nozzle at Mach number 1.4 are computed: one unheated jet with a Reynolds number of 150,000 and one heated jet with a Reynolds number of 76,000 and a temperature ratio of 1.75. Flow and noise results are compared with the experimental database fromNASAGlennResearchCenter. The nozzle is included in the computational domain.The present study shows that the results from the unstructured solver are in good agreement with the experimental data for time-averaged and fluctuating quantities, velocity spectra in the jet, and the sound obtained in the near field and the far field using the integration of the Ffowcs–Williams and Hawkings equation.