An implicit finite difference procedure for the laminar, supersonic base flow

The development of a tool for solving the near field of a scramjet fuel injector was attacked by first developing a numerical technique for solving the laminar, supersonic near wake flow. It was considered important to develop a procedure that had a potential for reduced computation time compared with explicit methods. The implicit numerical procedure was extended to mixed subsonic/supersonic flow with shocks, expansions, and regions of reverse flow. In the present case, numerical results have been obtained for the laminar, supersonic near wake behind a rectangular base. This numerical method produced stable, convergent, and accurate solutions when applied to this complex flow problem.