Aerodynamic Analysis of the Rifleman's Assault Weapon.

摘要

A wind tunnel test was conducted for seven different shell configurations. The basic configuration was a spherical shell with modification to the base section. A spherical aft shell, a truncated aft shell, and various artificial boundary layer trip devices on the base section was used. The test was conducted for Mach numbers up to 0.3 to determine the aerodynamic forces at angles-of-attack from -2 to 15 deg and various spin rates. Force and moment data were obtained for these runs. The magnus forces due to the velocity component normal to the spin axis were measured in terms of the side force coefficient CY. (Author)