Time-Accurate Computations of Free-Flight Aerodynamics of a Spinning Projectile With and Without Flow Control
Final rept. Mar 2005-Apr 2006
ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD WEAPONS AND MATERIALS RESEARCH DIRECTORATE
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This report describes a new multi-disciplinary computational study undertaken to compute the flight trajectories and simultaneously predict the unsteady free flight aerodynamics of a spinning projectile configuration with and without aerodynamic flow control. Actual flight trajectories are computed with an advanced coupled computational fluid dynamics CFD-rigid body dynamics RBD technique. An advanced time-accurate Navier-Stokes computational technique has been used in CFD to compute the unsteady aerodynamics associated with the free flight of the spinning projectile at subsonic speeds. Computed positions and orientations of the projectile have been compared with actual data measured from free flight tests and are found to be generally in good agreement. The same advanced coupled procedure has been used to compute the aerodynamics of the spinning projectile with flow control with the use of a synthetic microjet. Unsteady numerical results obtained from the coupled method show the flow field, the aerodynamic forces and moments, and the flight trajectories of the projectile.