Active Flow Control at Low Reynolds Numbers on a NACA 0015 Airfoil

larger than 0 . The primary objective of the experiment was to compare force and moment data obtained from integrating surface pressures to data obtained from a 5-component strain-gage balance in preparation for additional three-dimensional testing of the model. To achieve this objective, active ow control is applied at an angle of attack of 6 where published results indicate that oscillatory momentum coecients exceeding 1% are required to delay separation. Periodic excitation with an oscillatory momentum coecient of 1.5% and a reduced frequency of 0.71 caused a signicant delay of separation on the airfoil with a ap deection of 20 . Higher momentum coecients at the same reduced frequency were required to achieve a similar level of ow