A FILM COOLING EXPERIMENT ON A CONVERGENT-DIVERGENT NOZZLE

Abstract

A stainless steel, supersonic nozzle with an 11/16-in. -dian throat was successfully cooled using only a tangential air film. Mass fractions of cooling air film ranged from 0.190 to 0.302, and the maximum recorded wall temperature was 1800F. Stilling chamber pressures ranged from 482 to 577 psia and temperatures from 2615 to 3460F. Measured wall temperatures showed only limited agreement with a newly developed theory, with the theory underestimating adiabatic wall temperatures by from 20 to 30 percent.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1966
Accession Number
AD0634587

Entities

People

  • Dennis D. Horn
  • Henry F. Lewis

Organizations

  • Arnold Engineering Development Complex

Tags

DTIC Thesaurus Topics

  • Abstracts
  • Air Force
  • Arc Heaters
  • Civil Engineering
  • Contracts
  • Convergent Divergent Nozzles
  • Cooling
  • Engineering
  • Film Cooling
  • Governments
  • Heat Transfer
  • Nozzles
  • Payload
  • Stainless Steel
  • Steel
  • Supersonic Nozzles
  • Test Equipment

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow