COMPUTATIONAL FLUID DYNAMIC ANALYSIS OF THE CAN-1 HYPERSONIC RESEARCH PROJECTILE

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Authors
  1. Fournier, E.Y.
  2. Dupuis, A.D.
Corporate Authors
Defence Research Establishment Valcartier, Valcartier QUE (CAN)
Abstract
In an effort to broaden our knowledge based 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.
Keywords
Computational Fluid Dynamics;Flow separation
Report Number
DREV-TM-9607 — Technical Report
Date of publication
17 Jun 1996
Number of Pages
24
DSTKIM No
96-02566
CANDIS No
499218
Format(s):
Document Image stored on Optical Disk;Hardcopy

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