Abstract
Experimental geometry optimization techniques for high-lift airfoils are reported. A modern three-element airfoil model with a remotely actuated flap was designed, tested, and used in low-speed wind-tunnel experiments to investigate optimum flap positioning based on lift. Detailed results for lift coefficient vs flap vertical and horizontal position are presented for two airfoil angles of attack, 8 and 14 deg. Two automated optimization simulations, the method of steepest ascent and a sequential simplex method, were demonstrated using experimental data. A simple online optimizer was successfully demonstrated with the wind-tunnel model that automatically seeks the optimum lift as a function of flap position. Hysteresis in lift as a function of flap position was discovered when tests were conducted using continuous flow conditions
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