Aeroelastic response of a pitch-plunge airfoil with non-zero initial angle of attack

0493594 - ÚT 2019 CA eng C - Konferenční příspěvek (zahraniční konf.)
Šidlof, P. - Štěpán, M. - Vlček, Václav - Šimurda, David - Luxa, Martin - Horáček, Jaromír
Aeroelastic response of a pitch-plunge airfoil with non-zero initial angle of attack.
Proceedings of the 9th International Symposium on Fluid-Structure Interaction, Flow-Sound Interaction, Flow-Induced Vibration & Noise. Toronto: University of Guelph, 2018 - (Hassan, M.), č. článku FIV2018-152.
[International Symposium on Fluid-Structure Interactions, Flow-Sound Interactions, Flow-Induced Vibration & Noise /9./. Toronto (CA), 08.07.2018-11.07.2018]
Grant CEP: GA ČR(CZ) GA16-01246S
Institucionální podpora: RVO:61388998
Klíčová slova: aeroelasticity * airfoil flutter * Schlieren visualization
Obor OECD: Acoustics
https://fiv2018.com/ocs/index.php/fiv2018/fivcan/paper/viewFile/152/137

Flow-induced vibration of a NACA0015 airfoil model with pitch and plunge degrees of freedom has been studied in a wind tunnel at Re = 200,000 - 500,000 and M = 0 - 0.45. The model is supported by linear springs and replaceable torsional springs, yielding different pitch-to-plunge natural frequency ratios. The chord length is c = 59.5 mm, the elastic axis is located at c/3. For supercritical inflow velocities, the airfoil undergoes aeroelastic oscillations with relatively large amplitudes – in most cases deep dynamic stall with separated airflow, but sometimes a classical coupled-mode flutter with attached airflow. The study reports on pitch, plunge and dynamic pressure measurements and Schlieren visualizations of the flow field for the case of non-zero initial angle of attack, compared to previous measurements with zero initial incidence angle published in Journal of Fluids and Structures (Šidlof et al, 2016).
Trvalý link: http://hdl.handle.net/11104/0286932