THRUST NOZZLE OPTIMIZATION INCLUDING BOUNDARY LAYER EFFECTS.

Abstract

An optimization analysis, a numerical method, and a computer program for the design of optimum thrust nozzles including boundary layer effects are presented. The analysis is based on the assumptions that the flow is homentropic and that the boundary layer is thin. The problem is formulated to maximize the pressure thrust integral along the supersonic wall contour for a general isoperimetric constraint. The results of the optimization analysis are a set of hyperbolic partial differential equations for determining the Lagrange multipliers in the region of interest, and a set of algebraic equations for determining the initial and boundary conditions for these multipliers on the boundaries of the region. The numerical method employes a simplified relaxation technique which, it is felt, will encourage the use of this general design technique. A preliminary parametric study was conducted to determine the possible percent thrust improvement that can be obtained by the inclusion of the boundary layer effects. (Author)

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1967
Accession Number
AD0826167

Entities

People

  • H. Doyle Thompson
  • Joe D. Hoffman
  • M. Peter Scofield

Organizations

  • Purdue University

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Computer Programs
  • Computers
  • Differential Equations
  • Equations
  • Inclusions
  • Integrals
  • Layers
  • Optimization
  • Partial Differential Equations

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.
  • Operations Research

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers