Unsteady Airfoil with Dynamic Leading- and Trailing-Edge Flaps

摘要

A preliminary study of the control of the dynamic-load loops of an oscillating NACA 0015 airfoil via an 18%c LEF and a 25% c TEF, deflected dynamically and independently, was conducted at Re= 2.86 × 10~6. Both upward and downward deflections actuated at t_s = 0πn (or α_(mean)) were tested to maximize the effects of the flap motion on the behavior of the DSV. The results show that deflecting the LEF alone did not have as large an effect on airfoil performance as deflecting the TEF.