Improvements in the reliability and quality of unstructured hybrid mesh generation

• Published in: International journal for numerical methods in fluids Vol. 45; no. 1; pp. 79 - 108
• Main Authors: Ito, Yasushi, Nakahashi, Kazuhiro
• Format: Journal Article
• Language: English
• Published: Chichester, UK John Wiley & Sons, Ltd 10-05-2004; Wiley
• Subjects: Air transportation and traffic; Applied sciences; CFD; Computational methods in fluid dynamics; Exact sciences and technology; Fluid dynamics; Fundamental areas of phenomenology (including applications); Ground, air and sea transportation, marine construction; Physics; unstructured hybrid mesh; viscous flow simulations; Large Reynolds number; Wing; Airplane; Computational fluid dynamics; Digital simulation; Pressure distribution; Airfoils; Aircraft; Viscous fluids; Mesh generation
• ISSN: 0271-2091; 1097-0363
• DOI: 10.1002/fld.669

This paper presents a reliable and automated approach to the generation of unstructured hybrid grids comprised of tetrahedra, prisms and pyramids for high Reynolds number viscous flow simulations. To enhance robustness, the hybrid mesh generation process starts with the formation of an isotropic tetrahedral grid. Prismatic layers are then added on no‐slip walls fully automatically by obeying user‐specified boundary conditions and three parameters: the number of the layers, an initial layer thickness normal to the walls, and a stretching factor. Topological modifications to the original isotropic tetrahedral elements are prohibited during the layer generation process. The tetrahedral elements near no‐slip walls are shifted inward and the resulting gap between the tetrahedra and the walls is filled up with prismatic elements. To enhance the quality of the prismatic layers around sharp corners, two normals are evaluated for the marching process in these regions. The addition of prismatic elements is locally stopped if negative‐volume elements are created or not enough space is left. An angle‐based smoothing method ensures that the quality of the tetrahedral elements is retained for a reasonable computational cost. The method is demonstrated for two scaled experimental supersonic airplane models designed at the National Aerospace Laboratory of Japan (NAL). Numerical results are compared with wind tunnel experimental data. Copyright © 2004 John Wiley & Sons, Ltd.