Hypersonic Aerospace Vehicle Leading Edge Cooling Using Heat Pipe, Transpiration and Film Cooling Techniques

Abstract

An investigation was conducted to determine the feasibility of using liquid metal heat pipe, transpiration and film cooling techniques to cool aerospace vehicle leading edge structures exposed to severe, transient hypersonic flight aerodynamic heating environments. A finite difference, numerical cooling model was developed and applied to an aerospaceplane wing leading edge section and to a scramjet inlet section. It was demonstrated that these cooling techniques are feasible.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1991
Accession Number
ADA236406

Entities

People

  • James M. Modlin

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Boundary Layer
  • Boundary Layer Flow
  • Computational Fluid Dynamics
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Heat Energy
  • Heat Transfer
  • Hypersonic Aircraft
  • Hypersonic Vehicles
  • Liquids
  • Propulsion Systems
  • Ramjet Engines
  • Supersonic Combustion Ramjet Engines
  • Thermodynamics

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.
  • Thermal Physics or Thermal Science.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow
  • Space
  • Space - Hall-Effect Thruster