摘要
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。
By solving the compressible Navier-Stokes equations,a computational fluid dynamics（CFD）software is developed independently,which can well simulate the flow in the gap in hypersonic vehicle surface.An analytical study has been performed through this software to investigate the free stream parameters＇ effects on vortexes and aerodynamic heating environment of thermal protection tile transverse gaps.The results indicate that with the increase of free stream Reynolds number,the number of main vortexes increases,the shape of main vortexes becomes plumper,and the dimensional and non-dimensional heat flux increases;with the increase of free stream Mach number,the number and shape of main vortexes almost stay the same,the dimensional heat flux is increasing but the non-dimensional heat flux remain unchanged;with the increase of free stream angle of attack（comparatively low）,the change rules of vortexes and heat flux are basically the same with increasing free stream Reynolds number.So we know that the depth of the so-called ＂dead water zone＂greatly depends on the free stream Reynolds number and angle of attack.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2016年第3期761-770,共10页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(91216204)
国家"973"计划(2014CB744100)~~
关键词
来流参数
高超声速
缝隙
计算流体力学
旋涡
热流分布
inflow parameters
hypersonic
gap
computational fluid dynamics
vortex
heat-flux distribution
