Navier-Stokes Computations for a Spinning Projectile From Subsonic to Supersonic Speeds

Report No. ARL-TR-2850
Authors: Sidra I. Silton
Date/Pages: September 2002; 42 pages
Abstract: A computational study has been undertaken to predict the aerodynamic coefficients of a standard spinning projectile using a modern unstructured Navier-Stokes flow solver. Numerical and semi-empirical results have been obtained for a wide range of Mach numbers to include subsonic, transonic, and supersonic flight regimes. Effects of 0?, 2?, and 5? angles of attack have been investigated. Comparison of computational fluid dynamics results to both experimental range data and semi-empirical aeroprediction code results shows remarkably good agreement. Flow field characteristics of each flight regime are explored.
Distribution: Approved for public release
  Download Report ( 1.198 MBytes )
If you are visually impaired or need a physical copy of this report, please visit and contact DTIC.
 

Last Update / Reviewed: September 1, 2002