Euler and Navier-Stokes Simulation of the Aerodynamics of a Spinning Missile with Dithering Control Surfaces
Blades, E. L., Marcum, D., & Mitchell, B. (2002). Euler and Navier-Stokes Simulation of the Aerodynamics of a Spinning Missile with Dithering Control Surfaces. MSSU-COE-ERC-02-02: Mississippi State University.
Euler and Navier-Stokes solutions were obtained to predict the aerodynamic performance of a spinning missile with moving canards. Integrated force and moment coefficients were computed, along with helicity contours to track the vortices being generated by the canards. Comparisons were made to determine the effect of grid resolution and viscous effects. Different command levels for the canards were also examined. The grid resolution study was performed using 3 levels of refinement: coarse, medium, and fine. The results indicated that the force and moment coefficients generated using the medium refinement grid were in agreement with those using the fine grid. However, the finest grid increased the resolution of the vortices, particularly the canard root vortex. Comparison of the viscous and inviscid force and moment coefficients revealed that the viscous effects were not significant. The largest viscous contribution was to the axial force, which was approximately 10% of the total axial force. The main difference between the inviscid and viscous results is the resolution of the canard root vortex. Overall the viscous effects were minimal since the flow is supersonic and at this low angle of attack, the flow remains attached and there are no regions of separated flow where viscous effects are important.