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 CL=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.
High-lift design for a forward swept natural laminar flow wing
CEAS Aeronaut J
CEAS Aeronautical Journal ; 11 , 1 ; 81-92
2020-01-01
12 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
High-lift design for a forward swept natural laminar flow wing
Online Contents | 2019
|AIAA | 1980
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