An immersed boundary solver for inviscid compressible flows
An immersed boundary solver for inviscid compressible flows
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DOI：
10.1002/fld.4399
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发表时间：
2017-12
影响因子：
1.8
通讯作者：
Cheng Liu;Changhong Hu
中科院分区：
文献类型：
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作者：
Cheng Liu;Changhong Hu
本文开发了一种简单有效的浸入边界（IB）方法，用于非粘性可压缩欧拉方程的数值模拟。我们提出了一种基于坐标变换的方法来计算鬼点的未知数。在本研究中，身体网格截点用于构建完整的双线性（2-D）/三线性（3-D）插值。提出了一种带有新参考平滑度指标的三阶加权基本非振荡方案，以提高极值和不连续区域的精度。采用动态分块结构化自适应网格来提高计算效率。采用负载平衡的并行计算来节省 3D 问题的计算成本。数值测试表明，该方法具有二阶整体空间精度。双马赫反射测试表明，当前的 IB 方法给出了与边界拟合方法几乎相同的解。通过 NACA2012 翼型的亚音速和跨音速流动进一步验证了求解器的准确性。最后，通过模拟经过 3D ONERA M6 机翼的跨音速流，对当前采用自适应网格的 IB 方法进行了验证。获得了与实验和其他数值结果的总体一致性。
In this paper, a simple and efficient immersed boundary (IB) method is developed for the numerical simulation of inviscid compressible Euler equations. We propose a method based on coordinate transformation to calculate the unknowns of ghost points. In the present study, the body‐grid intercept points are used to build a complete bilinear (2‐D)/trilinear (3‐D) interpolation. A third‐order weighted essentially nonoscillation scheme with a new reference smoothness indicator is proposed to improve the accuracy at the extrema and discontinuity region. The dynamic blocked structured adaptive mesh is used to enhance the computational efficiency. The parallel computation with loading balance is applied to save the computational cost for 3‐D problems. Numerical tests show that the present method has second‐order overall spatial accuracy. The double Mach reflection test indicates that the present IB method gives almost identical solution as that of the boundary‐fitted method. The accuracy of the solver is further validated by subsonic and transonic flow past NACA2012 airfoil. Finally, the present IB method with adaptive mesh is validated by simulation of transonic flow past 3‐D ONERA M6 Wing. Global agreement with experimental and other numerical results are obtained.