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首页> 外文期刊>Journal of the Institution of Engineers (Inida) >Numerical Simulation of Shock Induced Turbulence in a Nozzle Flow
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Numerical Simulation of Shock Induced Turbulence in a Nozzle Flow

机译：喷嘴流中激流湍流的数值模拟

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摘要

In the present paper, a study has been conducted to investigate the shock induced turbulent flow fields and shock/turbulent-boundary layer interaction at the nozzle divergent. Experimental photographs and numerical images are used to investigate on laminar flow structures, transition phenomena, flow separation line as well as viscous boundary layer separation, turbulence structure development and shock/turbulent-boundary layer interaction. It is observed that transition from laminar to turbulent flow separation is shown earlier at the nozzle divergent for the weaker shock wave propagation and the fully developed turbulence is appeared with unsteady flow fluctuations at the end of the nozzle divergent. It is found that the pressure downstream of the separation point showed an unsteady behavior with strong oscillations, and finally jumped to values quite above the ambient pressure. By solving the 2D Navier-Stokes equations with κ-ε turbulence model, all turbulent parameters are determined at the end of the nozzle divergent and it is observed that turbulence intensities are almost uniform at the end of the nozzle divergent where slight decay phenomena are appeared along the downstream direction. The skewness of the velocity fluctuations indicates that the present flow appears to be isotropic at the end of the nozzle divergent.
机译：在本文中，已经进行了研究以研究在喷嘴发散处的冲击引起的湍流场和冲击/湍流-边界层相互作用。实验照片和数值图像用于研究层流结构，过渡现象，流分离线以及粘性边界层分离，湍流结构发展和冲击/湍流-边界层相互作用。可以观察到，在较慢的冲击波传播下，在喷嘴发散处显示了从层流到湍流分离的过渡，并且在喷嘴发散的末端出现了完全发展的湍流，并出现了不稳定的流量波动。结果发现，分离点下游的压力表现出不稳定的现象，并伴有强烈的振荡，最终跃升至远高于环境压力的值。通过用κ-ε湍流模型求解二维Navier-Stokes方程，在喷嘴发散的末端确定了所有湍流参数，并观察到在出现轻微衰减现象的喷嘴发散的末端，湍流强度几乎是均匀的沿下游方向。速度波动的偏斜度表明当前的流量在喷嘴发散的末端看起来是各向同性的。

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