35th AIAA Fluid Dynamics Conference and Exhibit

Simulation of Separation Control on a Morphing Wing with Conformal Camber

Vamsidhar Katam, Dept. of Mechanical Engineering, University of Kentucky

Raymond P. LeBeau, Dept. of Mechanical Engineering, University of Kentucky

rplebeau@engr.uky.edu

Jamey D. Jacob, Dept. of Mechanical Engineering, University of Kentucky

Jdjacob@engr.uky.edu

The aerodynamics of airfoils at low speeds is significantly altered by low Reynolds number effects. The general problem at these Reynolds numbers is the tendency towards separation which decreases lift and increases drag. Typical aircrafts affected by this Reynolds numbers are micro-aerial vehicles, unmanned aerial vehicles, and aircrafts flying in low density environments. The present paper focuses on flow control at low Reynolds numbers through oscillatory wing morphing. A modified NACA 4415 airfoil with an adaptive actuator mounted in it is taken as the primary airfoil for the present studies. This actuator can be kept static or oscillated to change the effective camber of the primary airfoil. The current paper focuses on the results obtained from experiments and numerical simulations of static and oscillatory actuator cases over different Reynolds numbers and a range of angles of attack. Comparisons will be made between the experiments and numerical simulation results thereby establishing the effectiveness of the present approach as a flow control mechanism.