Transonic inviscid/turbulent airfoil flow simulations using a pressure based method with high order schemes
Transonic inviscid/turbulent airfoil flow simulations using a pressure based method with high order schemes
复制标题
使用基于压力的方法和高阶方案进行跨音速无粘/湍流翼型流动模拟
DOI：
10.1007/3-540-59280-6_152
复制
发表时间：
1995
影响因子：
4.4
通讯作者：
E. Olsson
中科院分区：
文献类型：
--
作者：
Gang Zhou;L. Davidson;E. Olsson
本文介绍了基于压力的欧拉/纳维-斯托克斯求解器跨声速气动流动模拟的计算。在本工作中，重点关注QUICK、LUDS和MUSCL等高阶方案的实现。提出了一种新的对流近似格式CHARM。对NACA 0012型进行了无粘流动模拟。CHARM方案对目前的不粘情况有较好的解析度。对rae2822型进行了紊流计算。采用QUICK格式求解平均运动方程，并结合MUSCL格式求解k和e方程，得到了较好的结果。未观察到非物理振荡。结果还表明，二阶和三阶格式与实验数据相比具有相当的精度。
This paper presents computations of transonic aerodynamic flow simulations using a pressure-based Euler/Navier-Stokes solver. In this work emphasis is focused on the implementation of higher-order schemes such as QUICK, LUDS and MUSCL. A new scheme CHARM is proposed for convection approximation. Inviscid flow simulations are carried out for the airfoil NACA 0012. The CHARM scheme gives better resolution for the present inviscid case. The turbulent flow computations are carried out for the airfoil RAE 2822. Good results were obtained using QUICK scheme for mean motion equation combined with the MUSCL scheme for k and e equations. No unphysical oscillations were observed. The results also show that the second-order and thir-dorder schemes yielded a comparable accuracy compared with the experimental data.