Heat Transfer/Boundary Layer Investigation of Heating Discrepancies in Wind Tunnel Testing of Orbiter Insulating Articles.

Abstract

Wind tunnel test runs were conducted on Space Shuttle orbiter insulating articles. The data from one HRSI run was processed by a heat estimation program, revealing a large discrepancy in magnitude of the heat transfer coefficient over the HRSI tile when compared to that yielded by flat plate theory and thin skin results. An initial suggestion for the cause of this discrepancy was the nonisothermal wall effect.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1982
Accession Number
ADA124803

Entities

People

  • Peter T. Cappelano

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Boundary Layer
  • Boundary Layer Flow
  • Carbon Carbon Composites
  • Data Reduction
  • Equations
  • Heat Flux
  • Heat Transfer
  • Heat Transfer Coefficients
  • Low Temperature
  • Mach Number
  • Specific Heat
  • Stagnation Temperature
  • Surface Temperature
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Engineering.
  • Combustion and Flow Dynamics.
  • Theoretical Analysis.

Technology Areas

  • Microelectronics
  • Microelectronics - Graphene
  • Space
  • Space - Hall-Effect Thruster