Investigation of Boundary Layer and Performance Effects of Transpiration Cooling Through a Porous Plate in a Rocket Nozzle.

Abstract

This study used a range of low blowing ratios with air through an area of porous material in a Mach 2.0 nozzle to quantity the change in boundary layer thickness as a function of blowing ratio. Also, exit and wall Mach number profiles at each blowing ratio were collected to characterize performance losses as a result of blowing. Performance in terms of specific impulse was also studied. As expected, the boundary layer thickness increased and nozzle performance in terms of exit Mach number decreased with increasing blowing ratio.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1994
Accession Number
ADA289393

Entities

People

  • David N. Keener

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Human Systems
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Computer Programs
  • Engineering
  • Flow Fields
  • Fluid Flow
  • Fluid Mechanics
  • Gas Turbine Nozzles
  • Generators
  • Geometry
  • Heat Transfer
  • Mach Number
  • Pressure Measurement
  • Rocket Engines
  • Rocket Nozzles
  • Shock Tunnels
  • Specific Impulse

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Thermal Physics or Thermal Science.