JET INTERFERENCE DURING STAGE SEPARATION AT VERY HIGH ALTITUDES

Abstract

Pressure and force measurements were obtained on two upper stage and three lower stage missile models during simulated stage separation. The upper stage rocket engine exhaust was simulated with high pressure carbon dioxide. Data were also obtained at a limited number of test conditions using gaseous nitrogen to simulate the rocket engine exhaust. Data were obtained at ten separation distances with an upper stage nozzle exit pressure ratio variation from 5.5 to 12,914. The test cell pressure ranged from 1.2 to 6300 microns of mercury, which corresponds to an altitude range from 290,000 to 106,000 ft. The results indicate that interference on the upper stage is dependent on the lower stage configuration and upper stage chamber pressure and is independent of the ambient pressure.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1964
Accession Number
AD0439948

Entities

People

  • T. W. Binion Jr.

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Altitude
  • Base Pressure
  • Carbon Dioxide
  • Chambers
  • High Pressure
  • Instrumentation
  • Mach Number
  • Measurement
  • Nitrogen
  • Precision
  • Pressure Distribution
  • Pressure Gradients
  • Rockets
  • Secondary Flow
  • Static Pressure
  • Vacuum
  • Vacuum Chambers

Readers

  • Applied Combinatorial Optimization and Logic Circuit Design.
  • Fluid Dynamics.
  • Internal Combustion Engine (ICE) Technology.