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首页> 外文期刊>International Journal of Heat and Mass Transfer >Attached flow formed by opposing jet in hyper/supersonic flow
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Attached flow formed by opposing jet in hyper/supersonic flow

机译：通过超声波流动的相对喷射形成的附着流动

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In current paper, a numerical study by ANSYS FLUENT software has been carried out on the opposing jet in hyper/supersonic flow. In incoming Mach number 6, flow fields around two head-shape models, namely a hemisphere-cylinder and a cone-cylinder, are calculated, respectively. Air and helium of different temperatures as the injection gases were injected through the sonic nozzle at the nose of the model. In order to track the motion of the opposing jet, we employ the species transport model together with the axisymmetric Navier-Stokes equations as the physical model. And find, due to the effect of the bow shock on the opposing jet, the opposing jet flows back and form an attached flow instead of the incoming high temperature air tightly around the model surface, which effectively achieve the wall heat reduction. Moreover, the higher the incoming Mach number, the more significant the percentage reduction of the wall heat transfer rate is. Helium injection has more advantageous than air injection at lower total pressure ratios. The position and size of the recirculation vortex formed by the opposing-jet attached flow have the direct relationship with the fluctuation range of wall characteristic parameters. The smaller the ratio of the model geometric curvature and recirculation size, the smaller the fluctuation amplitudes of wall characteristic parameters are. By adjusting the injection gaseous parameters, it is hopeful to control the near-wall flow features and the aircraft head-shape conversions. (C) 2019 Elsevier Ltd. All rights reserved.
机译：在目前的论文中，在超声波流量的相对喷气机上对ANSYS流利软件进行了数值研究。在进入马赫号6中，分别计算出两个头形模型的流场，即半球缸和锥缸。随着注射气体的不同温度的空气和氦气通过模型的鼻子的声音喷嘴注入。为了跟踪相对射流的运动，我们使用物种传输模型与轴对称Navier-Stokes方程一起作为物理模型。并且发现，由于弓形冲击对相对射流的影响，相对的喷射器向后流回并形成附着的流量而不是紧紧地围绕模型表面紧密地进行进入的高温空气，这有效地实现了壁散热。而且，进入马赫数越高，壁传热速率的降低百分比越大。氦注射比在较低总压力比下的空气喷射更有利。通过相对射流连接的流动形成的再循环涡流的位置和尺寸与壁特性参数的波动范围的直接关系。模型几何曲率和再循环尺寸的比率越小，壁特性参数的波动幅度越小。通过调节注射气态参数，希望控制近壁流特征和飞机头部转换有望。 （c）2019 Elsevier Ltd.保留所有权利。

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