Numerical and parametric study of MVGs on a UAV geometry in subsonic flow

Abstract

This work details how numerical methods can be employed to determine the optimal arrangement of multiple micro vortex generators (MVG) installed on a UAV wing with its flaps deflected/deployed. For very little cost, the use of MVGs can substantially improve the aerodynamic performance of the UAV by increasing the lift and reducing the drag, particularly during critical phases of the flight (takeoff and landing). The optimal position, related to the detachment zone, and height, related to the boundary layer, of a vortex generator is studied numerically by solving the three dimensional Navier-Stokes equations in a simplified configuration. The numerical study includes a reference baseline configuration. A parametric study is then performed to determine, which configuration gives the maximum gain—highest lift/drag ratio. A preliminary numerical study of convergence for different grids to ensure convergency of the solutions is included. Finally, considering these results, a selection of the optimal configurations based on the aerodynamic performance and the manufacturing limitations.