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针对高超声速飞行器表面缝隙内部流动,通过求解可压缩Navier-Stokes方程,自主研发了一套能够较好模拟缝隙流动特性的计算流体力学(CFD)软件。利用该软件研究了来流参数对防热瓦横缝旋涡结构及热环境的影响。计算结果表明:随着来流雷诺数的增加,缝内旋涡结构呈现主涡个数增多形态趋于饱满的变化趋势,缝隙壁面绝对热流和无量纲热流增加;随着来流马赫数的增加,缝内主涡个数、形态基本不变,但主涡旋转速度增加,缝隙壁面绝对热流增加,无量纲热流基本不变;随着来流迎角的增加(迎角较小时),缝内旋涡结构和热流变化规律基本与增加来流雷诺数相同。由此分析可知,涡量向下传递并形成旋涡的距离,即形成所谓“死水区”的深度,主要由来流雷诺数和来流迎角决定。
In order to solve the compressible Navier-Stokes equations, a set of computational fluid dynamics (CFD) software, which can simulate the characteristics of the gap flow well, is developed independently for the internal flow in the surface of the hypersonic vehicle. The software was used to study the effect of flow parameters on the vortex structure and thermal environment of the anti-heating tile. The results show that with the increase of the Reynolds number, the vortices in the seams show a tendency of full vorticity increasing, and the absolute and non-dimensional heat flux in the crevice increases. With the increase of Mach number, However, the rotational velocity of the main vortex increases and the absolute heat flow increases in the slit wall, and the dimensionless heat flow remains basically unchanged. With the increase of the incoming angle of attack (when the angle of attack is small), the vortex in the slit The change of structure and heat flow is basically the same as that of increasing the flow Reynolds number. From this analysis, it can be seen that the distance that the vorticity transmits downward and forms the vortex, that is, the depth of the so-called “stagnant water”, is mainly determined by the Reynolds number of the incoming flow and the incoming flow angle of attack.