PROJECT SQUID. An Evaluation of the Heat Transfer Encountered in a Rocket Motor Operating at High Chamber Pressures

Abstract

The theoretical rates of heat transfer between the walls of a five hundred-pound thrust rocket motor and the combustion gases resulting from the oxidation of octane and aniline by white fuming nitric acid are obtained as a function of the rocket motor chamber pressure. The convective heat transfer coefficients, obtained by using the McAdams correlation, are compared with the rates obtained by the Humble, Lowdermilk, Grele correlation. The radiant heat transfer rates are obtained by the Hottle, Egbert method. It was found that the chamber and nozzle heat transfer rates increase linearly with chamber pressure and that the nozzle heat transfer rates become extremely high at chamber pressures beyond 1500 psia.

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Document Details

Document Type
Technical Report
Publication Date
Jul 20, 1949
Accession Number
ADA952956

Entities

People

  • C. F. Warner
  • M. J. Zucrow

Organizations

  • Purdue Research Foundation

Tags

DTIC Thesaurus Topics

  • Air Force
  • Carbon Dioxide
  • Combustion Chambers
  • Engineering
  • Fluid Flow
  • Heat Transfer
  • Heat Transfer Coefficients
  • Jet Engine Fuels
  • Jet Propulsion
  • Liquid Rocket Oxidizers
  • New York
  • Partial Pressure
  • Physical Properties
  • Reynolds Number
  • Rocket Engines
  • Thermal Conductivity
  • United States

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Petroleum Engineering
  • Rocket Propulsion.