An Implicit Finite Difference Procedure for the Laminar, Supersonic Base Flow.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO
Pagination or Media Count:
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 subsonicsupersonic 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.
- Fluid Mechanics
- Combustion and Ignition