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

Result code in IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F46747885%3A24220%2F19%3A00006179" target="_blank" >RIV/46747885:24220/19:00006179 - isvavai.cz</a>
Alternative codes found
RIV/46747885:24620/19:00006179
Result on the web
<a href="http://www.fiv2018.com/ocs/index.php/fiv2018/fivcan/paper/view/152" target="_blank" >http://www.fiv2018.com/ocs/index.php/fiv2018/fivcan/paper/view/152</a>
DOI - Digital Object Identifier
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Result language
angličtina
Original language name
Aeroelastic response of a pitch-plunge airfoil with non-zero initial angle of attack
Original language description
Flow-induced vibration of a NACA0015 airfoil model with pitch and plunge degrees of freedom has been studied in a wind tunnel. 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 both in pitch and plunge. The study reports on vibration 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. The results suggest that a deep dynamic stall instability with fully separated airflow, which eventually develops for supercritical flow velocities, is initially triggered by a classical coupled-mode flutter instability.
Czech name
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Czech description
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Project
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Continuities
I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Publication year
2019
Confidentiality
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

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