Optimization of Supersonic Rocket Nozzles with Viscous Flow.
MASSACHUSETTS UNIV AMHERST
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The determination of the optimum shape of a supersonic rocket motor nozzle, under the constraint of a given surface area, while taking into account the effects of viscous action and heat conduction, is the objective of the investigation. In the case of a nozzle low density or low Reynolds number where the effects of viscous action and heat conduction extend over the entire flow field, the optimization problem for a conical nozzle was solved on the basis of postulated similar solutions. For more general application, where a thin boundary layer can be postulated, the optimization of a contoured axisymmetric nozzle was undertaken by adopting one of two approaches, namely one involving a physical boundary layer region and another involving the displacement thickness of the boundary layer. In both cases, it is the objective to consider the inviscid and the viscous regions governed by appropriate flow equations simultaneously in determining the necessary conditions. This method of subjecting two simply-connected regions simultaneously to optimization is developed for the first time and can be extended in many directions. Author
- Fluid Mechanics
- Rocket Engines