Compressible Turbulence Measurement in Low-Angle Injection into a Supersonic Flow.

Abstract

Mean flow and compressible turbulence measurements have been obtained at two stations downstream of low-angle supersonic injection into a Mach 3.0 flow (Re/m = 15 x 106). Data were collected using conventional Pitot and cone-static probes, single and multiple overheat cross-wire anemometry, and flow visualization techniques (shadowgraphs and schlierens). A direct measure of total Reynolds shear stress was accomplished using a turbulence transformation of the Reynolds-averaged Navier-Stokes equations. Results show compressibility effects, indicated by density fluctuations, to be large relative to the velocity fluctuations and on the same order in all three components. Compressibility appears to account for as much as 75% of the total Reynolds shear. The results of the present study suggest turbulent compressibility effects are very important for this class of flows. (MM)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1995
Accession Number
ADA293836

Entities

People

  • Gregory J. Mccann

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Chemical Oxygen Iodine Lasers
  • Computational Fluid Dynamics
  • Computational Science
  • Equations
  • Flow
  • Flow Visualization
  • Fluid Flow
  • Low Angles
  • Measurement
  • Navier Stokes Equations
  • Shear Stresses
  • Static Pressure
  • Supersonic Combustion Ramjet Engines
  • Supersonic Flow
  • Turbulent Flow
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.
  • Materials Science and Engineering.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers