The Effect of Microcylinder Shape on Enhancing the Aerodynamics of Airfoils at a Low Reynolds Number
Passive flow control around airfoils, wind turbines, and submarines to enhance their aerodynamic properties is the subject of interest in several studies. Previous research provides different solutions, from basic changes in surface roughness and simple geometries to complex shapes and mechanical so...
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2024-12-01
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| Series: | Energies |
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| Online Access: | https://www.mdpi.com/1996-1073/18/1/66 |
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| author | Renata Gnatowska Karolina Gajewska |
| author_facet | Renata Gnatowska Karolina Gajewska |
| author_sort | Renata Gnatowska |
| collection | DOAJ |
| description | Passive flow control around airfoils, wind turbines, and submarines to enhance their aerodynamic properties is the subject of interest in several studies. Previous research provides different solutions, from basic changes in surface roughness and simple geometries to complex shapes and mechanical solutions. This article presents experimental research using the Particle Image Velocimetry (PIV) method on a NACA 0012 airfoil at a Reynolds number of 66,400. Initially, the airfoil was tested for three different angles of attack: 13°, 15°, 17°, and 19°. These tests revealed that angles of attack above 15° significantly increase boundary layer detachment, as shown in the normalized streamwise velocity fields <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><msub><mi>U</mi><mi>x</mi></msub></semantics></math></inline-formula>. In the second stage of the research, a different-shaped microcylinder with a characteristic dimension (d/c) of 0.01 was added to the leading edge of the airfoil at a high angle of attack of 17°. Unlike traditional vortex generators placed at the rear of the airfoil, this configuration aimed to reduce boundary layer detachment. The experiment demonstrated that the microcylinder effectively reduced boundary layer detachment at this angle of attack. |
| format | Article |
| id | doaj-art-8146f8b91ecf4116b1988cf24654d76a |
| institution | Kabale University |
| issn | 1996-1073 |
| language | English |
| publishDate | 2024-12-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Energies |
| spelling | doaj-art-8146f8b91ecf4116b1988cf24654d76a2025-01-10T13:16:59ZengMDPI AGEnergies1996-10732024-12-011816610.3390/en18010066The Effect of Microcylinder Shape on Enhancing the Aerodynamics of Airfoils at a Low Reynolds NumberRenata Gnatowska0Karolina Gajewska1Department of Thermal Machinery, Czestochowa University of Technology, Al. Armii Krajowej 21, 42-200 Czestochowa, PolandDepartment of Thermal Machinery, Czestochowa University of Technology, Al. Armii Krajowej 21, 42-200 Czestochowa, PolandPassive flow control around airfoils, wind turbines, and submarines to enhance their aerodynamic properties is the subject of interest in several studies. Previous research provides different solutions, from basic changes in surface roughness and simple geometries to complex shapes and mechanical solutions. This article presents experimental research using the Particle Image Velocimetry (PIV) method on a NACA 0012 airfoil at a Reynolds number of 66,400. Initially, the airfoil was tested for three different angles of attack: 13°, 15°, 17°, and 19°. These tests revealed that angles of attack above 15° significantly increase boundary layer detachment, as shown in the normalized streamwise velocity fields <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><msub><mi>U</mi><mi>x</mi></msub></semantics></math></inline-formula>. In the second stage of the research, a different-shaped microcylinder with a characteristic dimension (d/c) of 0.01 was added to the leading edge of the airfoil at a high angle of attack of 17°. Unlike traditional vortex generators placed at the rear of the airfoil, this configuration aimed to reduce boundary layer detachment. The experiment demonstrated that the microcylinder effectively reduced boundary layer detachment at this angle of attack.https://www.mdpi.com/1996-1073/18/1/66airfoilNACA 0012microcylindersparticle image velocimetrywind turbine blade |
| spellingShingle | Renata Gnatowska Karolina Gajewska The Effect of Microcylinder Shape on Enhancing the Aerodynamics of Airfoils at a Low Reynolds Number Energies airfoil NACA 0012 microcylinders particle image velocimetry wind turbine blade |
| title | The Effect of Microcylinder Shape on Enhancing the Aerodynamics of Airfoils at a Low Reynolds Number |
| title_full | The Effect of Microcylinder Shape on Enhancing the Aerodynamics of Airfoils at a Low Reynolds Number |
| title_fullStr | The Effect of Microcylinder Shape on Enhancing the Aerodynamics of Airfoils at a Low Reynolds Number |
| title_full_unstemmed | The Effect of Microcylinder Shape on Enhancing the Aerodynamics of Airfoils at a Low Reynolds Number |
| title_short | The Effect of Microcylinder Shape on Enhancing the Aerodynamics of Airfoils at a Low Reynolds Number |
| title_sort | effect of microcylinder shape on enhancing the aerodynamics of airfoils at a low reynolds number |
| topic | airfoil NACA 0012 microcylinders particle image velocimetry wind turbine blade |
| url | https://www.mdpi.com/1996-1073/18/1/66 |
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