A generic spinning missile with dithering canards is used to demonstrate the utility of an overset structured grid approach for simulating the aerodynamics of rolling airframe missile systems. The approach is used to generate a modest aerodynamic database for the generic missile. The database is populated with solutions to the Euler and Navier-Stokes equations. It is used to evaluate grid resolution requirements for accurate prediction of instantaneous missile loads and the relative aerodynamic significance of angle-of-attack, canard pitching sequence, viscous effects, and roll-rate effects. A novel analytical method for inter- and extrapolation of database results is also given.
Aerodynamic Analysis of a Spinning Missile with Dithering Canards
2003
29 pages
Report
No indication
English
Aerodynamics , Aircraft , Aerodynamic characteristics , Dithers , Missile systems , Missile configurations , Canard configurations , Maneuverability , Spin dynamics , Airframes , Computerized simulation , Vortices , Grid refinement(Mathematics) , Pitching moments , Spatial resolution , Flow distribution
Aerodynamic Analysis of a Spinning Missile with Dithering Canards
Online Contents | 2004
|