Effects of mesh resolution on hypersonic heating prediction
Effects of mesh resolution on hypersonic heating prediction
复制标题
网格分辨率对高超声速加热预测的影响
DOI：
10.1063/2.1102201
复制
发表时间：
2011
影响因子：
3.4
通讯作者：
Fan Jing
中科院分区：
文献类型：
--
作者：
Sun Quanhua;Zhu Huiyu;Wang Gang;Fan Jing
气动加热预测是高超声速飞行器设计和优化的关键问题。一个挑战是Navier-Stokes方程的解强烈依赖于计算网格。本文研究了网格分辨率对热流密度预测的影响。结果表明，采用细网格可以得到与网格无关的解，其精度得到了动力学粒子模拟结果的证实。分析了网格引起的数值误差主要来自边界层通量计算，而表面温度梯度可以用壁面函数计算。因此，建议采用边界层捕获能力强的数值格式进行高超声速加热预报。
Aeroheating prediction is a challenging and critical problem for the design and optimization of hypersonic vehicles. One challenge is that the solution of the Navier-Stokes equations strongly depends on the computational mesh. In this letter, the effect of mesh resolution on heat flux prediction is studied. It is found that mesh-independent solutions can be obtained using fine mesh, whose accuracy is confirmed by results from kinetic particle simulation. It is analyzed that mesh-induced numerical error comes mainly from the flux calculation in the boundary layer whereas the temperature gradient on the surface can be evaluated using a wall function. Numerical schemes having strong capability of boundary layer capture are therefore recommended for hypersonic heating prediction.
影响因子：
5.6
作者：
J. Longo
通讯作者：
J. Longo
影响因子：
5
作者：
P. Papadopoulos;E. Venkatapathy;D. Prabhu;M. Loomis;D. Olynick
通讯作者：
P. Papadopoulos;E. Venkatapathy;D. Prabhu;M. Loomis;D. Olynick