SECONDARY GAS INJECTION IN A CONICAL ROCKET NOZZLE. 1. EFFECT OF ORIFICE DIAMETER AND MOLECULAR WEIGHT IN INJECTANT

Abstract

Data are presented on interference forces resulting when a gas at ambient temperature is laterally injected through a single circular orifice in the conical portion of a rocket nozzle into hot supersonic propellent gases. Variables examined are injectant orifice size and associated pressure ratio change and effect of injectant molecular weight and specific heat ratio. Other parameters remain essentially constant during these tests. Simple theoretical arguments can predict relative effects of intrinsic injectant properties, but pressure ratio effects are not adequately described. Effectiveness of secondary injection depends on injectant orifice size, which was not treated in any theoretical modes.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1962
Accession Number
AD0275463

Entities

People

  • A. R. Stone
  • M. Shandor
  • R. E. Walker

Organizations

  • Johns Hopkins University

Tags

DTIC Thesaurus Topics

  • Boundary Layer
  • Carbon Dioxide
  • Exhaust Gases
  • Flow Rate
  • Gas Turbine Nozzles
  • Mach Number
  • Mass Flow
  • Molecular Weight
  • Pressure Measurement
  • Propellants
  • Rocket Engines
  • Rocket Nozzles
  • Secondary Injection
  • Standards
  • Static Pressure
  • Supersonic Flow
  • Two Dimensional

Readers

  • Combustion and Flow Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow