Numerical Study of Supersonic Flows Using Different Techniques.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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The purpose of this work was to obtain the solution to three supersonic flow problems using three different numerical techniques. First, a shockboundary layer problem is solved using MacCormacks explicit technique. Then, using the same technique a shrouded rocket nozzle problem is solved. These two problems showed that the explicit scheme required many minutes of computer time to solve. In order to explore more efficient codes to solve the shroud problem, space marching algorithms were studied. A space marching algorithm using flux-splitting in the streamwise direction was applied to an approximate form of the Navier-Stokes equation. Flux-splitting combined with a global interation approach should allow the shroud problem to be solved with a space marching algorithm. The flux-splitting code was applied to two supersonic flow problems and very good results were obtained. Author Theses.
- Fluid Mechanics
- Rocket Engines