Experiments and Analysis Related to External Burning for Propulsion

Abstract

The results of first year's efforts on an experimental base flow program are reported. The design and checkout for a Mach 3.0 axisymmetric wind tunnel with a model base diameter of 2.25 inches is described, as well as the automated data acquisition system. Experiments are reported on detailed static pressures for the diffuser wall, model wall and base and near wake. Temperature measurements are presented to establish a near adiabatic wall condition. The relationship between the experimental program and propulsive external burning is discussed.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1976
Accession Number
ADA024984

Entities

People

  • Douglas H. Neale
  • James E. Hubbartt
  • Walter W. Wilson
  • Warren C. Strahle

Organizations

  • Georgia Tech

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes
  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Air Force Facilities
  • Base Flow
  • Base Pressure
  • Boundary Layer
  • Combustion
  • External Burning
  • Flow
  • Fluid Dynamics
  • Hydrodynamics
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Test Facilities
  • Turbulent Mixing
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.
  • Rocket Propulsion.