Navier-Stokes Simulations of the Aerodynamics of a Missile with a Free-Spinning Tail
Blades, E. L., & Marcum, D. (2003). Navier-Stokes Simulations of the Aerodynamics of a Missile with a Free-Spinning Tail. MSSU-COE-ERC-03-05: Mississippi State University.
Navier-Stokes solutions were obtained to predict the aerodynamic performance of a missile with a free-spinning tail. 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. The grid resolution study was performed using three levels of refinement. Examination of the force and moment coefficients revealed that the viscous effects were not insignificant at these conditions. The largest viscous contribution was to the axial force, which was approximately 17% of the total axial force. There are also large viscous contributions to the pitching moment at certain orientations due to interactions with the vortices generated by the canards. The viscous contribution to the other force and moment coefficients was less than 3% and it was also found that these viscous contributions are independent of the spin rate. Multiple tail spin rates were examined and only the rolling moment was affected by the spin rate. A tail spin rate of 1940 rpm was found to be the spin rate at which zero net rolling moment is produced. It was also determined that at these conditions, the vortices generated by the canards do impinge on the spinning tail.