摘要
Quadtree-based Cartesian grid was automatically generated from specified geometry.Adaptive refinements were performed according to geometric parameters and solution of flow field.An altered CCST(curvature corrected symmetry technique)approach was proposed to apply solid wall boundary conditions. Driven flows in a square cavity and flows around NACA0012airfoil were simulated and compared with the result of published structured grid and stretched Cartesian grid.The results show that solid wall boundary condition are accurately applied by current altered CCST approach,while incompressible/compressible subsonic, transonic and supersonic viscous flows are adequately simulated with adaptively refined Cartesian grid.
Quadtree based Cartesian grid was automatically generated from specified geometry. Adaptive refinements were performed according to geometric parameters and solution of flow field. An altered CCST （curvature corrected symmetry technique） approach was proposed to apply solid wall boundary conditions. Driven flows in a square cavity and flows around NACA0012 airfoil were simulated and compared with the re sult of published structured grid and stretched Cartesian grid. The results show that solid wall boundary condi tion are accurately applied by current altered CCST approach, while incompressible/compressible subsonic, transonic and supersonic viscous flows are adequately simulated with adaptively refined Cartesian grid.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2014年第2期467-474,共8页
Journal of Aerospace Power
