A high-order large eddy simulation (LES) code based on the flux reconstruction (FR) scheme is further developed for supersonic jet simulation. The FR scheme provides an efficient and easy-to-implement way to achieve high-order accuracy on an unstructured mesh. The order of accuracy and the shock capturing capability of the solver are validated with the isentropic Euler vortex and Sod’s shock tube problem. A heated under-expanded supersonic jet case from NASA’s Small Hot Jet Acoustic Rig (SHJAR) database is used for validation. The turbulence statistics along the nozzle centerline and lip-line are examined. We predict the acoustic radiation with the Ffowcs Williams and Hawkings method, which is integrated with our solver. The far-field acoustic predictions show reasonable agreement with the experimental measurement in the upstream and downstream directions, where the shock-associated noise and the large-scale turbulent mixing noise are dominant, respectively.

中文翻译：

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用于超音速射流声学预测的高阶大涡模拟求解器的验证

进一步开发了基于通量重建（FR）方案的高阶大涡模拟（LES）代码，用于超音速射流模拟。FR 方案提供了一种高效且易于实现的方法来在非结构化网格上实现高阶精度。通过等熵欧拉涡和索德激波管问题验证了求解器的精度顺序和冲击捕获能力。来自 NASA 小型热喷射声学钻机 (SHJAR) 数据库的加热欠膨胀超音速喷射箱用于验证。检查沿喷嘴中心线和唇线的湍流统计。我们使用与我们的求解器集成的 Ffowcs Williams 和 Hawkings 方法预测声辐射。