Flowfield Near Liquid Fuel Jets Injected Transverse to a Hot Supersonic Air Stream.

Abstract

This paper presents the first results of a study aimed at delineating the processes leading to ignition of liquid fuel jets injected transverse to a hot supersonic air stream. The tests were conducted at Mach 1.8 with a nominal stagnation pressure of 100 psia and stagnation temperatures from 500-1800 F. Kerosene, CS2 and water were used as the injectants. The observations were in the form of direct, top-view photos, temperature measurements and top-view, infrared Thermographic photos to produce isotherm patterns. Attention was directed, in particular, at the surface layer formed on the wall near the injection port. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1975
Accession Number
ADA050635

Entities

People

  • Joseph A. Schetz
  • William J. Mcvey

Organizations

  • Virginia Tech

Tags

Communities of Interest

  • Materials and Manufacturing Processes
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Temperature
  • Cameras
  • Combustion
  • Engineering
  • Flow
  • Flow Fields
  • Flow Rate
  • Ignition
  • Images
  • Isotherms
  • Liquid Jets
  • Measurement
  • Photographs
  • Photography
  • Pressure Measurement
  • Stagnation Pressure
  • Stagnation Temperature

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Oceanography.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow