Smart rotors

Dynamic-stall load control by means of an actuated flap

Journal article (2018)

Authors

M. Raiola Carlos III University of Madrid
Stefano Discetti Carlos III University of Madrid
A. Ianiro Carlos III University of Madrid
F. Samara University of Waterloo
F. Avallone Wind Energy - Aerospace Engineering
D. Ragni Wind Energy - Aerospace Engineering
Research Group
Wind Energy (Aerospace Engineering) (TU Delft)
Copyright: © 2018 M. Raiola, Stefano Discetti, A. Ianiro, F. Samara, F. Avallone, D. Ragni
DOI
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https://doi.org/10.2514/1.J056342
More Info
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Published Date

2018

Language

English

Reuse Rights

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Faculty

Aerospace Engineering

Department

Flow Physics and Technology

Research Group

Wind Energy

Abstract

This study focuses on an active strategy for unsteady-load control by means of a trailing-edge flap. Experiments on a 2D pitching and heaving NACA 0018 airfoil with an actuated trailing-edge flap are performed at a reduced frequency κ = 0.1 in a free-stream flow with Re = 1.3 × 105. The model is equipped with 24 differential pressure transducers to provide with the time-resolved distribution of the pressure difference between pressure and suction sides. Results show that an actuated flap significantly decreases the magnitude of unsteady loads. A reduced order model of the flap effect on the loads is proposed. The loads are estimated by adding the contribution of the clean wing with the flap one. This model can be applied to unsteady loads for both attached flow and dynamic stall conditions, constituting an effective control strategy for dynamic loads, if the airfoil transition location is properly controlled.