Independent Stage Control of a Cascade Injector (Postprint)

Abstract

An experimental investigation of a cascade injector was completed. The objective of this investigation was to determine whether the number of active stages in the cascade injector could be used to control penetration and mixing characteristics. The injector was tested at two overexpanded injection conditions in a Mach 3 crossflow. Shadowgraph and schlieren imaging, Mie scattering, Planar Laser Induced Fluorescence, and pressure profiling were the diagnostic techniques used to reveal various features of the injectant plume and its interaction with the supersonic crossflow. Results suggest that penetration can be controlled by the number of active stages in the cascade injector. Additional analysis and experiments are planned to better quantify the effects of injector stages revealed in this initial work.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 2006
Accession Number
ADA464054

Entities

People

  • C. D. Carter
  • D. R. Eklund
  • E. J. Gutmark
  • H. L. Meicenheimer
  • K.-y. Hsu
  • M. R. Gruber

Organizations

  • University of Cincinnati

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Combustion
  • Flow Rate
  • Fluid Mechanics
  • Fluorescence
  • Fuel Injection
  • Injectors
  • Laser Induced Fluorescence
  • Lasers
  • Mass Flow
  • Mie Scattering
  • Nitrogen Oxides
  • Research Facilities
  • Scattering
  • Test Facilities
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Combustion and Flow Dynamics.

Technology Areas

  • Directed Energy
  • Hypersonics
  • Hypersonics - Hypersonic Flow