Abstract
In this paper, the multi-objective 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 take-off setting to the landing setting. Therefore, design space is defined with satisfying its requirement. Slat is considered zero-gap. Objective function considered here are to maximize the lift to drag (I/d) minimize the drag co-efficient (C_d) at nose up angle, respectively. Then, maximum lift condition is also considered, therefore other objective functions are to maximize maximum lift-coefficient (C_<lmax>) and maximize the angle of attack that becomes C_<lmax>. 16 samples are selected by Latin hypercube sampling method and they are evaluated using Reynolds Averaged Navier-Stokes Simulation (RANS). After this evaluation, Kriging models are constructed for each objective functions and the decision making (DM) is carried out with applying self-orgnizing map (SOM).
