High-lift design for a forward swept natural laminar flow wing

Abstract

The scope of the paper is to present the results of a RANS-based aerodynamic high-lift design for a natural laminar flow wing with negative sweep. The chosen high-lift system consists of a Krueger leading edge flap with shielding function and a fixed-vane trailing edge flap. The design was first optimized in two main wing sections and then verified by 3D RANS simulations of a wing-body model. Finally, engines were added to the geometric model to estimate the high-lift performance of the landing configuration. With a maximum lift coefficient of C_L,max=2.85 for the wing-body model with engine, the target from the preliminary aircraft design was reached. Further potential for improvement was found in the optimization strategy and the shape of the fuselage--wing junction.