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首页> 外文期刊>Journal of Aerospace Sciences and Technologies >COMPUTATIONAL INVESTIGATION OF SUPERSONIC JET SCREECH IN CIRCULAR JETS USING HIGHER-ORDER WENO SCHEME
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COMPUTATIONAL INVESTIGATION OF SUPERSONIC JET SCREECH IN CIRCULAR JETS USING HIGHER-ORDER WENO SCHEME

机译：基于高阶Weno格式的圆射流超声速射流计算研究

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摘要

Computational investigation of supersonic jet screech in imperfectly expanded circular jets is conducted using higher order Weighted Essentially Non-Oscillatory (WENO) scheme based solution of the axisymmetric Navier Stokes equations. The jet screech phenomenon is numerically simulated for an over expanded and an under expanded circular supersonic jet. Sound pressure levels, screech amplitude and frequency are calculated from the pressure history in the flow field and compared with values in literature. Shock cell spacings in the high speed jet are also extracted from numerical simulations and compared with that in literature. Important aspects of a screeching jet observed experimentally, like the interaction of instability waves with the shock train and the contribution of downstream propagating hydrodynamic fluctuations to the creation of the upstream moving acoustic wave in the acoustic feedback mechanism, are also captured in the present computations. The latter phenomenon has been observed experimentally but not reported previously in numerical simulations.
机译：使用基于轴对称Navier Stokes方程的高阶加权基本非振荡（WENO）方案对不完全膨胀的圆形喷嘴中的超音速射流尖叫进行了计算研究。对超音速和超音速圆形超音速射流的射流尖叫现象进行了数值模拟。根据流场中的压力历史记录计算声压级，尖锐振幅和频率，并将其与文献中的值进行比较。高速射流中的冲击单元间距也从数值模拟中提取出来，并与文献进行了比较。在实验中观察到的急流喷射的重要方面，如不稳定波与冲击波的相互作用以及下游传播的水动力波动对声反馈机制中上游移动声波的产生的贡献，也被捕获在当前计算中。后一种现象已通过实验观察到，但先前未在数值模拟中报告。

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