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首页> 外文期刊>Journal of Aerospace Sciences and Technologies >NUMERICAL COMPUTATION OF HEAT TRANSFER ON REENTRY CAPSULES AT MACH 5
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NUMERICAL COMPUTATION OF HEAT TRANSFER ON REENTRY CAPSULES AT MACH 5

机译：马赫数为5的再入舱内传热的数值计算

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摘要

The heat transfer over various reentry axisymmetric configurations is studied numerically by solving time-dependent compressible laminar Navier-Stokes equations. The governing fluid flow equations are disrectized in spatial coordinates employing a finite volume approach, which reduces the equations to semi-discretized ordinary differential equations. Temporal integration is performed using multi-stage Runge-Kutta time stepping scheme. A local time step is used to achieve steady state solution. The numerical simulation is carried out on a mono-block structured grid. The numerical computation is carried out for freestream Mach number of 5.0. The numerical scheme captures well all the essential flow field features such as bow shock wave, sonic line, expansion fan on the corner, recompression shock wave and recirculating flow in the base region. Comparisons of the flow field, surface pressure, skin friction coefficient and wall heat flux results are made between different configurations of the reentry capsules such as ARD (ESA's Atmospheric Reentry Demonstrator), CARINA, Apollo, Muses-C (Mu Science Engineering Satellite), OREX (Orbital Reentry Experiments) and Beagle-2. The effects of geometrical parameters of the different reentry capsules on surface pressure, skin friction coefficients and heat flux and forebody aerodynamic drag are analyzed. Base pressure is independent of the forebody shape of the reentry capsules. The effects of module geometry on the flow field are numerically analyzed which may be useful for optimization of the reentry capsule.
机译：通过求解与时间相关的可压缩层流Navier-Stokes方程，数值研究了各种折返轴对称结构上的热传递。控制流体流方程采用有限体积方法在空间坐标中分解，从而将方程简化为半离散的常微分方程。时间积分是使用多阶段Runge-Kutta时间步进方案执行的。使用本地时间步长来实现稳态解决方案。数值模拟是在整体结构的网格上进行的。对于5.0的自由流马赫数进行数值计算。数值方案很好地捕获了所有基本的流场特征，例如弓形冲击波，声波线，拐角处的膨胀风扇，再压缩冲击波和基础区域中的再循环流。比较了不同构型的再入舱之间的流场，表面压力，皮肤摩擦系数和壁热通量结果，例如ARD（ESA的大气再入演示器），CARINA，Apollo，Muses-C（Mu科学工程卫星）， OREX（轨道再入实验）和Beagle-2。分析了不同再入舱的几何参数对表面压力，皮肤摩擦系数，热通量和前体气动阻力的影响。基本压力与折返胶囊的前体形状无关。数值分析了模块几何形状对流场的影响，这可能对优化再入舱很有用。

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