Physics and control of the flow over a generic trapezoidal wing planform

This work provides discussion of key geometric features that influence the aerodynamic performance of trapezoidal wings. Subject of the survey is a highly tapered wing model with low aspect ratio, based on a NACA0012 airfoil section. A comparison to a non-tapered swept-back wing demonstrates advantageous stability properties that motivate this work. Experimentally obtained force and moment data, surface flow visualization and PIV are presented along with computational results. It is found that the strength and formation of the leading-edge vortex can be altered by modifying the nose radius or droop of the model. Implications of those changes on integral aerodynamic properties are evaluated. A triangular and a parallel flap geometry that exhibit fundamentally different flow conditions are discussed. Focus is placed on the latter to account for non-aerodynamic requirements of typical military aircraft. The capability of sweeping jet actuators to redirect or attach flow is assessed to examine the resulting effects on forces and moments. Additionally, the possibility of applying active flow control as a means to maneuver is explored.