|Project Name||Funding Body||Industrial Partners||Academic/Research Partners||Duration|
|Delta Wing Aeroelasticity||N/A||N/A||Multibody and Mechatronic Systems Lab - University of Liège, Department of Engineering - Istanbul University||2008-2010|
Limit cycle oscillations involving Delta wings are an important area of research in modern aeroelasticity. Such phenomena can be the result of geometric nonlin- earity, aerodynamic nonlinearity or under-wing store nonlinearity. A series of investigations of Delta Wing aeroelasticity by several researchers have demonstrated that low speed LCOs can be obtained as a result of the interaction of structural geometric nonlinearity with attached flow aerodynamics.
The purpose of the present research is to determine experimentally to what extent struc- tural and/or aerodynamic nonlinearities are important in causing Limit Cycle Oscillations of a Delta wing at different steady angles of attack.
A flexible Delta wing model in the ULg wind tunnel
A demonstration of Delta wing Limit Cycle Oscillations
Exciting a subcritical LCO