Computational modeling of the aerodynamics and flight mechanics of maneuvers of an UAV induced by variable-incidence wings

The aerodynamics and flight mechanics of the dynamic maneuver of a low speed propeller powered puller-type Unmanned Aerial Vehicle (UAV) have been modeled by solving the unsteady incompressible Navier-Stokes equations and the six-DOF rigid body flight dynamics equations together. The flight maneuver of this UAV is accomplished by swiveling the outboard wings relative to the inboard wing fixed to the fuselage to change the angle of attack towards stall angle to slow down the UAV for symmetric as well as asymmetric flight conditions. To set the stage for a computational aero-mechanics modelling, the performance characteristics of a propeller are assessed numerically. Along with time accurate studies, standard UAV aerodynamic characteristics are modeled on the basis of high fidelity computational aerodynamics and the flight trajectory of the UAV considering the variation of aerodynamic characteristics during the flight maneuver is computed as part of the overall computed solution by coupling the aerodynamics and flight dynamics.