Detonation Tube Conditions for Simulating: RP-1/LOX and Various Amine/ N2O4 Rocket Engine Plumes

Abstract

The report documents the running conditions necessary to simulate RP- 1/LOX and various Amine/N2O4 rocket engine plumes using the Grumman Detonation Tube Facility to reproduce the chemical and thermodynamic state properties of the rocket engine combustion chamber. Absolute measurements of shortwave infrared (SWIR) radiation from a variety of plumes are being obtained. The propellant combinations being investigated are UDMH/N2O4, A-50/N2O4, RP-1/LOX, and H2/O2.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1973
Accession Number
AD0771067

Entities

People

  • J. Leng
  • M. W. Slack

Organizations

  • Grumman

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Chambers
  • Combustion
  • Combustion Chambers
  • Contracts
  • Detonation Waves
  • Engines
  • Fluid Dynamics
  • High Pressure
  • Liquid Oxygen
  • Measurement
  • Nozzle Area Ratio
  • Nozzles
  • Propellants
  • Radiation
  • Rocket Engines
  • Shock Tubes
  • Simulations

Fields of Study

  • Physics

Readers

  • Computational Modeling and Simulation
  • Image Processing and Computer Vision.
  • Rocket Propulsion.