Free-flight range tests and numerical computations of a power-law elliptic cross-section projectile

Abstract

This paper presents computational and experimental aerodynamic data of a power-law elliptic cross-section projectile at Mach numbers ranging from 3.0 to 5.0. The experimental data consisted of nine free-flight projectiles launched within an instrumented facility. The computational work was carried out via the Cobalt60 code at the flight conditions of the experimental facility. The results indicate good agreement between the experimental and computational data determined in this effort as well as with engineering level predictions. The free-flight data was limited to small angles of attack so high fidelity determination of the aerodynamic stability coefficients and derivatives was not possible. Discrepancies were seen in the center of pressure data between the experimental and the computational data and require further investigation.