Numerical Studies on the Aerodynamics of a High-Speed Spinning Projectile

The projectile during travel inside gun barrel, after firing, has varying flow physics over it from subsonic to supersonic regime. The quantitative investigation of boundary layer over the spinning cone was done numerically by changing different parameters using Ansys fluent code. The parameters considered for study was Mach number, Reynolds number as well as Strouhal number. Boundary layer thickness as well as pressure increases with increasing Strouhal number. The decrease in Reynolds number increases the boundary layer thickness up to 1 mm. Effect of spin at high Mach number is within 0.05 mm whereas the density and velocity were seen to be varied up to 0.5 mm thickness.