Abstract
This chapter presents results obtained in a numerical investigation to determine the effect of the Gurney flap on a NACA 23012 airfoil. Two-dimensional models for the airfoil with different Gurney flap deployment and retraction position due to the motion imparted by the actuators are studied from the geometric data of the PZL Sokol W-3 main rotor section with appropriate flow boundary conditions. The flapped airfoil section aerodynamic coefficient from the numeric simulation is compared with numerical data for the clean airfoil. Different deployment and retraction position of the Gurney flap are studied to evaluate the aerodynamic characteristics and the force required to hold the Gurney flap in different position by the piezoelectric actuators. The dynamic characteristics of the clean and flapped airfoil for a pitching airfoil are compared to ascertain the advantages.
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