Bipropellant Engine Plume Contamination Program. Volume 2. Chamber Measurements. Phase 2

Abstract

A bipropellant rocket engine plume contamination test program was conducted in the AEDC Aerospace Chamber (10V). A 5-lbf-thrust rocket engine, burning MMH as the fuel and N2O4 as the oxidizer, was operated over a range of engine operating parameters in a cryogenically pumped vacuum chamber where the background pressure was maintained below 0.00001 torr. Using the electron beam fluorescence technique, species number densities and rotational temperature were measured in both the forward- and back-flow region of the plume exhaust. Additionally, Mie scattering measurements were performed for the forward-flow regions of the plume exhaust.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1979
Accession Number
ADA077435

Entities

People

  • H. M. Powell
  • L. L. Price
  • R. E. Alt

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Combustion
  • Combustion Chambers
  • Control Systems
  • Data Acquisition
  • Electron Beams
  • Engineering
  • Light Scattering
  • Measurement
  • Mie Scattering
  • Propellants
  • Radiation
  • Refractive Index
  • Rocket Engines
  • Rocket Propulsion
  • Scattering
  • United States

Fields of Study

  • Physics

Readers

  • Aerosol Science/Aerosol Physics
  • Combustion and Flow Dynamics.
  • Rocket Propulsion.

Technology Areas

  • Directed Energy
  • Directed Energy - Lasers
  • Microelectronics
  • Space
  • Space - Hall-Effect Thruster