Abstract
The aerodynamic behavior of two classes of non-axisymmetric projectile geometries is parametrically investigated through computational fluid dynamic simulations. The sliced and bent configurational asymmetries examined are both denned by two parameters: an incidence angle and a pivot point location. The performance of each design has been evaluated by a trim lift figure of merit derived from static aerodynamic coefficients. The aerodynamic characteristics of the augmented projectiles have been computed with a three-dimensio nal structured Navier-Stokes solver, which has been validated against experimental results for both distributed and integrated quantities. The results show that the bent configuration is more effective than the sliced configuration due the larger volumetric asymmetry generated by the bend. The results also show that the effects of the pressure recovery from the high-pressure asymmetry surface dominate the performance of both configurations.
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