[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.
Disciplines :
Aerospace & aeronautics engineering
Author, co-author :
Rothkegel Ide, José Ignacio ; Université de Liège - ULiège > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale
Dimitriadis, Grigorios ; Université de Liège - ULiège > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale
Language :
English
Title :
Interactive boundary layer calculation of separated flows around 2D airfoils
Publication date :
27 June 2011
Event name :
International Forum on Aeroelasticity and Structural Dynamics, IFASD 2011
Event organizer :
Association Aéronautique Astronautique de France (3AF) Council of European Aerospace Sciences (CEAS) American Institute of Aeronautics and Astronautics
Event place :
Paris, France
Event date :
from 26-06-2011 to 30-06-2011
Audience :
International
Main work title :
Proceedings of the 15th International Forum on Aeroelasticity and Structural Dynamics, IFASD 2011
