Effects of Liquid Transpiration Cooling on Heat Transfer to the Diverging Region of a Porous-Walled Nozzle

Abstract

This research effort investigated the effects of evaporation of water on the heat transferred to the wall of the diverging portion of a porous walled nozzle The AFIT High Pressure Shock Tube was used with a two-dimensional Mach 3 nozzle. One flat surface of the nozzle was fitted with a layer of porous stainless steel from the nozzle throat to the exit. This porous material was saturated with water to simulate liquid transpiration cooling. Surface temperature data was taken in this region using fast response coaxial thermocouple. Heat transfer was determined from the surface temperature history. Data was taken for stagnation pressures ranging from 2.0 to 5.2 MPa. The effectiveness of the cooling diminished with increasing stagnation conditions. Reduction in convection heat transfer coefficient ranged from 10% at higher stagnation pressures to 130% at the lowest stagnation pressure tested.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1997
Accession Number
ADA336722

Entities

People

  • Daniel J. Schieb

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Energy and Power Technologies
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Combustion Chambers
  • Computer Programs
  • Energy Transfer
  • Heat Transfer
  • Heat Transfer Coefficients
  • High Pressure
  • Materials
  • Measurement
  • Porous Materials
  • Rocket Engines
  • Shock Tubes
  • Shock Tunnels
  • Stagnation Pressure
  • Surface Temperature
  • Temperature Gradients
  • Two Dimensional

Readers

  • Combustion and Flow Dynamics.