Computational Fluid Dynamic Analysis of the CAN-1 Hypersonic Research Projectile

Abstract

In an effort to broaden our knowledge base on hypersonic aerodynamics, DREV conducted a Computational Fluid Dynamics (CFD) analysis of a hypersonic projectile, and successfully validated the analysis with results from free flight trials. Quantitative information (aerodynamic coefficients, shock wave interaction position, separation bubble position, etc.) was accurately obtained by the CFD code, as indicated by the good agreement with experimental results. The influence of the shock wave/flare interaction on some of these quantities was also identified. On the qualitative side, the modelling of flow characteristics such as shock patterns and positions, flow separation effects, etc. in a hypersonic environment has been accomplished. In addition, comparisons between these results and those from a numerical analysis from the Defence Research Agency (DRA) have shown that they provide similar values.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1996
Accession Number
ADA634678

Entities

People

  • A. D. Dupuis
  • E. Y. Fournier

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Coefficients
  • Computational Fluid Dynamics
  • Flow Separation
  • Fluid Dynamics
  • Free Flight
  • Information Operations
  • Numerical Analysis
  • Projectiles
  • Shock
  • Shock Waves
  • Transient Response Analysis

Readers

  • Computational Fluid Dynamics (CFD)
  • Defense Technology Research and Development.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow