DETERMINATION OF LOCAL EXPERIMENTAL HEAT-TRANSFER COEFFICIENTS ON COMBUSTION SIDE OF AN AMMONIA-OXYGEN ROCKET

Abstract

Local experimental heat-transfer coefficients were measured in the chamber and throat of a nominal 600-psia chamber pressure, 2400-lbthrust ammonia-oxygen rocket engine using three injector configurations. The rocket engine was run over a range of O/F and chamber pressure. The injector that achieved the best performance also produced the highest rates of heat flux at design conditions. The heat-transfer data from this injector agreed well with the simplified equation developed by Bartz at the throat region. A large spread of data observed for the chamber was attributed generally to the variations of combustion processes. The spread was least evident with the best-performing injector. (Author)

Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1961
Accession Number
AD0262929

Entities

People

  • Curt H. Liebert
  • Robert C. Ehlers

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Coefficients
  • Combustion
  • Engines
  • Equations
  • Heat Flux
  • Heat Transfer
  • Heat Transfer Coefficients
  • Injectors
  • Rocket Engines
  • Rockets

Readers

  • Combustion and Flow Dynamics.