Reference : Interactive boundary layer calculation of separated flows around 2D airfoils
Scientific congresses and symposiums : Paper published in a book
Engineering, computing & technology : Aerospace & aeronautics engineering
http://hdl.handle.net/2268/94925
Interactive boundary layer calculation of separated flows around 2D airfoils
English
Rothkegel Ide, José Ignacio [Université de Liège - ULg > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale >]
Dimitriadis, Grigorios mailto [Université de Liège - ULg > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale >]
27-Jun-2011
Proceedings of the 15th International Forum on Aeroelasticity and Structural Dynamics, IFASD 2011
Paper number IFASD-2011-014
No
No
International
International Forum on Aeroelasticity and Structural Dynamics, IFASD 2011
from 26-06-2011 to 30-06-2011
Association Aéronautique Astronautique de France (3AF)
Council of European Aerospace Sciences (CEAS)
American Institute of Aeronautics and Astronautics
Paris
France
[en] Aeroelasticity ; Interactive Boundary Layer ; Panel Methods
[en] Stall flutter is an important undesirable phenomenon affecting lifting surfaces such as helicopter and wind turbine blades, but is particularly difficult to model. Existing methodologies are not universally applicable, and have significant limitations concerning applicability, time of computation and accuracy. This paper presents a method that combines interactive boundary layer with point vortex shedding. It is applied to a NACA0012 airfoil, at different angles of attack in the −40◦ < a < 40◦ range, considering a free flow velocity of 20[m/s]. Results are compared to those obtained at the Goldstein Laboratory of the University of Manchester.
Researchers ; Professionals
http://hdl.handle.net/2268/94925
http://www.ifasd2011.com/

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