Simulation of Compressible Inviscid Flow on Adaptive Remeshing Unstructured Meshes. G.U. Aero Report 9424

An upwinding flux difference splitting method has been used to solve the Euler equations for compressible, inviscid flow on adaptive remeshing unstructured meshes. The method is a cell-centered, finite volume scheme with a Point-Gauss-Seidel (PGS) implicit time-stepping procedure. The high-order resolution has been achieved both by linear reconstruction of the variables and MUSCL approach. The advancing front technique (AFT) has been used to generate the unstructured mesh. The adaptive remeshing procedures based on a series of successive analysis of flow has been used to improve the quality of simulation. The mesh adaptation is accomplished by regeneration using information provided by the computed solution on the current mesh. The approach is demonstracted for four flow field simulations, namely transonic flow over two airfoils and hypersonic flow over a cylinder and blunt body