Computational Fluid Dynamic Analysis of the Base Cavity Interactions of the CAN-4 Research Projectile
Abstract
The aerodynamics of a cone-cylinder-flare projectile at high supersonic speeds has been investigated through computational means, and the results compared with existing experimental results from DREV's aeroballistic range. Aerodynamic coefficients, base pressure surveys, base flow visualization and shock patterns over the projectile were investigated for a Mach number range of 3.5 to 5.75. A goal of this investigation was the numerical study of the effects of a base cavity on the aerodynamic behavior of this projectile. Quantitative and qualitative information was accurately modelled by the CFD code as indicated by correlations between experimental and numerical values. The results seem to indicate an independence between the aerodynamic coefficients (aerodynamic coefficients constitute some of the major parameters of this study) and the presence of a base cavity for this particular configuration.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1997
- Accession Number
- ADA634677
Entities
People
- Alain D. Dupuis
- Eric Y. Fournier