An Experimental study on boundary layer separation control over s809 airfoil using synthetic jet actuators

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Date

2013

Author

Gül, Melika

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This thesis presents the results of an experimental study that investigates the effect of periodic excitation from individually controlled synthetic jet actuators on the separated shear layer and wake of a model wing that has S809 airfoil profile. The synthetic jet array consists of three individually controlled synthetic jet actuators driven by piezoelectric diaphragms located at 28% chord location near the middle of the span of the blade. In the first part of the study, hot wire and surface pressure measurements are conducted without synthetic jet actuators as a baseline case at Reynolds numbers, namely 2.3x105, 3.4x105 and 5.1x105, at zero angle of attack. The objective is to resolve the size and characteristics of separated shear layer and wake. Afterwards, the effect of the synthetic jet actuators on the separated shear layer and wake is investigated at 2.3x105 Reynolds number at zero angle of attack. Results show that periodic excitation from the synthetic jet actuators is effective in eliminating laminar separation bubble. In addition, this study provides information about flow physics related to the interaction between the synthetic jet flow and the adverse pressure gradient laminar boundary layer.

Subject Keywords

Aerofoils., Actuators., Boundary layer control., Wind turbines.

URI

http://etd.lib.metu.edu.tr/upload/12616595/index.pdf
https://hdl.handle.net/11511/23050

Collections

Graduate School of Natural and Applied Sciences, Thesis

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Citation Formats

M. Gül, “An Experimental study on boundary layer separation control over s809 airfoil using synthetic jet actuators,” M.S. - Master of Science, Middle East Technical University, 2013.