A Parametric Study of Boundary Layer Effects on Maximum Thrust Nozzle Contours.

Abstract

An optimization analysis employing the calculus of variations and a numerical relaxation scheme for applying the results are presented for the design of optimum, axisymmetric thrust nozzle contours including boundary layer effects. The method is illustrated by comparison with a known solution without boundary layer effects. A parametric study of boundary layer effects for a range of parameters typical of scramjet operation is presented. (Author)

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1969
Accession Number
AD0862771

Entities

People

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

Organizations

  • Purdue University

Tags

DTIC Thesaurus Topics

  • Axisymmetric
  • Boundaries
  • Boundary Layer
  • Calculus
  • Calculus Of Variations
  • Layers
  • Mathematics
  • Optimization
  • Supersonic Combustion Ramjet Engines

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Calculus or Mathematical Analysis