Aerodynamic Design of Helicopter Rotor Airfoil in Forward Flight Using Response Surface Method

This paper describes an efficient and robust optimization method for helicopter rotor airfoil design in forward flight. Navier-Stokes analysis was employed to compute the dynamic response of an airfoil, which simulates the unsteady rotor flow-field in forward flight. The optimization system consists of two categories; Response Surface Method to construct the response surface model based on D-optimal 3-level factorial design, and Genetic Algorithm to obtain the optimum solution of a defined objective function including penalty terms of constraints. The influence of design variables and their interactions on the aerodynamic performance was examined through the optimization processḕ倀ༀ㘲㠮ㄵ㬶㈷⸱㈳㬅K䍄乍츗ጊ᐀Ѐ㘲㜻Ԁ䭃䑎䶹6㈰㬅K䍄乍ꐗᘍ餀܀㘲㜮〵㬅K䍄乍