Accession Number:

ADA634678

Title:

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

Descriptive Note:

Technical memo

Corporate Author:

DEFENCE RESEARCH ESTABLISHMENT VALCARTIER (QUEBEC)

Personal Author(s):

Report Date:

1996-06-01

Pagination or Media Count:

41.0

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 waveflare 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.

Subject Categories:

  • Ammunition and Explosives
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE