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ISSN オンライン: 2642-0554

INVESTIGATION OF WING STALL DELAY EFFECT DUE TO AN UNDULATING LEADING EDGE: AN LES STUDY

Alex Skillen
Computational Fluid Dynamics group, Modelling and Simulation Centre, School of MACE, The University of Manchester, UK

Alistair Revell
Computational Fluid Dynamics group, Modelling and Simulation Centre, School of MACE, The University of Manchester, UK

Julien Favier
Laboratoire de Mécanique, Modélisation et Procédés Propres (M2P2), Aix-Marseille Université UMR7340 CNRS, 13451 Marseille, France

Alfredo Pinelli
School of Engineering and Mathematical Science, City University London

Ugo Piomelli
Dept. of Mechanical Engineering University of Maryland College Park, MD 20742, USA; Department of Mechanical and Materials Engineering Queen's University, Kingston (ON) K7L 3N6, Canada

要約

We present LES simulations of the flow over a wing with sinusoidal leading edge undulations. The undulations act as a passive flow control device, offering superior poststall aerodynamic performance relative to the unmodified wing with the same mean chord. The baseline case of a regular wing is also presented for comparison. In all cases the Reynolds number based on bulk velocity and mean chord is equal to 120, 000, and the angle of attack is set to 20°.
The study explores the details of the flow physics and the mechanisms by which the post-stall aerodynamic benefit is gained. For the particular set of geometrical and aerodynamic parameters considered, a hitherto unreported physical mechanism by which the undulation offers their benefit is observed. This increased understanding of the flow physics for the current configuration is an important step towards a more general understanding and the incorporation of the technology into practical designs. Potential applications include vertical axis wind turbines, unmanned air vehicles, helicopter blades, and canard surfaces; the present Reynolds number is of particular relevance to the first two of these applications.