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

摘要

A computational study has been undertaken to predict the aerodynamic coefficients of a standard spinning projectile using a modem 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 00, 20, and 50 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.