It is well recognised that C-grids are ideally suited for computing flows about bodies with a rounded leading edge like aerofoils. A branch cut line is an essential feature of such a grid and is usually treated as one of the boundaries. However, when one computes an incompressible flow using a pressure correction method, the presence of such a feature can be problematic in achieving a stable convergence. This paper describes a novel way of handling the branch cut line which ensures convergence of solution when using SIMPLEC type pressure correction procedures.
|Number of pages||5|
|Journal||Lecture Notes in Physics|
|Publication status||Published - 1995|