Navier-Stokes Computation of Shock Tube Exit Jet for Non-Ideal Blast Simulations.

Abstract

A computational fluid dynamics study of the exit jet of the U.S. Army Research Laboratory's 1.68-m diameter shock tube is presented. The shock tube exit jet provides a test environment in which to assess vehicle response to non-ideal blast. In the present study, time-accurate Navier-Stokes solutions are generated to simulate a shock tube exit jet test in which pressure probe measurements were obtained. The computational results are compared to the experimental data, as well as to analytical results and other empirical data. An examination is made of the jet flow field structure, and the computational accuracy and requirements are assessed.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1996
Accession Number
ADA308306

Entities

People

  • Bernard J. Guidos
  • Dale K. Ota
  • Stephen J. Schraml

Organizations

  • United States Army Research Laboratory

Tags

DTIC Thesaurus Topics

  • Accuracy
  • Computational Fluid Dynamics
  • Experimental Data
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Jet Flow
  • Measurement
  • Military Research
  • Shock Tubes
  • Tubes

Fields of Study

  • Physics

Readers

  • Computational Fluid Dynamics (CFD)
  • Fluid Dynamics.