Accession Number : AD0716859

Title :   Optimization of Supersonic Rocket Nozzles with Viscous Flow.

Descriptive Note : Final rept.,

Corporate Author : MASSACHUSETTS UNIV AMHERST

Personal Author(s) : Hwang,H. U. ; Murthy,S. N. B.

Report Date : OCT 1970

Pagination or Media Count : 152

Abstract : 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)

Descriptors :   (*ROCKET NOZZLES, OPTIMIZATION), (*SUPERSONIC NOZZLES, AERODYNAMIC CONFIGURATIONS), BOUNDARY LAYER, THERMAL CONDUCTIVITY, AXIALLY SYMMETRIC FLOW, THICKNESS, VISCOSITY, THRUST

Subject Categories : Aerodynamics
      Fluid Mechanics
      Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE