Abstract
The static rolling aerodynamics of a finned slender body is numerically studied in this paper. Simulation results show a nonlinear uprising of the rolling moment when the angle of attack is greater than 20° in subsonic flows. Asymmetric vortex break down phenomenon on the “horizontal” rudders is found to be responsible for this phenomenon. By introducing the geometric-equivalent angle of attack and geometric-equivalent sweep angle, the cause of the nonlinear rolling moment characteristics can be explained by the delta wing vortex breakdown analysis.
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