Abstract
In this paper, the design optimization of a high-lift airfoil consisted with a slat, a main wing and a flap is considered for a take-off condition. The design parameters are the elements' setting. Leading edge device, slat, should be deployed with the continuous motion from the setting for take-off to the setting for landing condition. Therefore, design space is defined with satisfying its requirement Slat is considered zero-gap. Objective function considered here is to minimize the drag co-efficient (C_d) at a target lift co-efficient (C_l) which satisfies the FAR regulation. 16 samples are selected by Latin hypercube sampling method and they are evaluated using Reynolds Averaged Navier-Stokes Simulation (RANS). After this evaluation, Kriging model is constructed and the minimum C_d point is explored by Genetic Algorithm (GA).
