An Aerodynamic Analysis of a Spinning Missile with Dithering Canards

摘要: A generic spinning missile with dithering canards is used to demonstrate the utility of an overset structured grid approach for simulating aerodynamics rolling airframe systems. convergence study andassessment viscous effects shows that a medium-resolution 8 million points provides good compromise between solution accuracy and throughput. Viscous should be included in detailed studies capture interaction inboard canard vortex fuselage tail boundary layers. The computed results agree well experimental data. database cases variation angle attack strength control authority pitch-up maneuver evaluate performance. case throughput rates are sufficient contemplate population aerodynamic databases Navier-Stokes computations. Overall, enables accurate efficient simulation configurations involve relative motion system components.