ZURUECK HOCH VOR INHALT SUCHEN

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Proposing Institution

Lehrstuhl für Aerodynamik, TU München
Project Manager

Dr.-Ing. Stefan Hickel
Boltzmannstraße 15
85748 Garching
Abstract
Highly swept wings frequently referred to as delta wings due to their triangular form are used in a variety of industrial applications, such as highly agile aircraft. At high angles of attack, delta wings can generate higher lift than rectangular wings with better stability and control characteristics. This is a consequence of the vortical flowfield on the upper side of the wing which is dominated by two large counter-rotating vortices starting from the leading edge. The flow separates from the leading edge and forms a curved free shear layer above the suction side of the wing, which eventually rolls up around a core. The very low pressure in the vortex core generates additional lift force on the delta wing. Steadiness and stability of these leading edge vortices is essential for controllability, particularly for highly agile aircraft. Therefore, the occurrence of unsteady vortex breakdown is critical and, since not fully understood, further investigation is needed. A profound understanding requires a comprehensive insight into the complete unsteady flowfield. This insight can only be obtained from time-accurate simulations accompanied by experiments. Our solver INCA (solver of the Incompressible Navier-Stokes equations on Cartesian Adaptive grids) offers the prediction-ability and efficiency-increasing features for this in-depth numerical study. INCA is efficiently parallelized and can largely exploit the exceptional computational resources provided by a Large-Scale project of the Gauss-Center of Supercomputing. This study will be an important step for the application of Implicit Large-Eddy Simulation to complex aerodynamic flows. High benefits are expected from a close collaboration with leading experimentalists.

Impressum, Conny Wendler