Circulation Control as a Roll Effector for Unmanned Combat Aerial Vehicles
This paper reports on a numerical investigation of the use of trailing edge circulation control as a roll effector on a generic unmanned combat aerial vehicle: the DLR F19 stability and control configuration. The Coanda effect induced by fluidic injections at the trailing edge of a wing is used to increase circulation and generate lift. Reynolds averaged Navier Stokes predictions are validated against wind tunnel experiments conducted at the Georgia Institute of Technology and NASA's basic aerodynamic research tunnel on an airfoil employing trailing edge circulation control. Two turbulence models are used: the Wilcox k o model and Menter's shear stress transport, showing that the Wilcox k o model provides the best comparisons with the experimental data. Baseline data for the stability and control configuration with conventional control surfaces from wind tunnel experiments done at the low speed wind tunnel owned by the German Dutch Wind Tunnels foundation (DNW NWB) are used to ensure the correct flow fea.