Flow Control around the UAS-S45 Pitching Airfoil Using a Dynamically Morphing Leading Edge (DMLE): A Numerical Study
This paper investigates the effect of the Dynamically Morphing Leading Edge (DMLE) on the flow structure and the behavior of dynamic stall vortices around a pitching UAS-S45 airfoil with the objective of controlling the dynamic stall. An unsteady parametrization framework was developed to model the...
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MDPI AG
2023-01-01
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| Series: | Biomimetics |
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| Online Access: | https://www.mdpi.com/2313-7673/8/1/51 |
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| author | Musavir Bashir Nicola Zonzini Ruxandra Mihaela Botez Alessandro Ceruti Tony Wong |
| author_facet | Musavir Bashir Nicola Zonzini Ruxandra Mihaela Botez Alessandro Ceruti Tony Wong |
| author_sort | Musavir Bashir |
| collection | DOAJ |
| description | This paper investigates the effect of the Dynamically Morphing Leading Edge (DMLE) on the flow structure and the behavior of dynamic stall vortices around a pitching UAS-S45 airfoil with the objective of controlling the dynamic stall. An unsteady parametrization framework was developed to model the time-varying motion of the leading edge. This scheme was then integrated within the Ansys-Fluent numerical solver by developing a User-Defined-Function (UDF), with the aim to dynamically deflect the airfoil boundaries, and to control the dynamic mesh used to morph and to further adapt it. The dynamic and sliding mesh techniques were used to simulate the unsteady flow around the sinusoidally pitching UAS-S45 airfoil. While the <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>γ</mi><mo>−</mo><mi>R</mi><msub><mi>e</mi><mrow><mi>θ</mi><mo> </mo></mrow></msub></mrow></semantics></math></inline-formula> turbulence model adequately captured the flow structures of dynamic airfoils associated with leading-edge vortex formations for a wide range of Reynolds numbers, two broader studies are here considered. Firstly, (i) an oscillating airfoil with the DMLE is investigated; the pitching-oscillation motion of an airfoil and its parameters are defined, such as the droop nose amplitude (<inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>A</mi><mi>D</mi></msub></mrow></semantics></math></inline-formula>) and the pitch angle at which the leading-edge morphing starts (<inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>M</mi><mrow><mi>S</mi><mi>T</mi></mrow></msub></mrow></semantics></math></inline-formula>). The effects of the <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>A</mi><mi>D</mi></msub></mrow></semantics></math></inline-formula> and the <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>M</mi><mrow><mi>S</mi><mi>T</mi></mrow></msub></mrow></semantics></math></inline-formula> on the aerodynamic performance was studied, and three different amplitude cases are considered. Secondly, (ii) the DMLE of an airfoil motion at stall angles of attack was investigated. In this case, the airfoil was set at stall angles of attack rather than oscillating it. This study will provide the transient lift and drag at different deflection frequencies of 0.5 Hz, 1 Hz, 2 Hz, 5 Hz, and 10 Hz. The results showed that the lift coefficient for the airfoil increased by 20.15%, while a 16.58% delay in the dynamic stall angle was obtained for an oscillating airfoil with DMLE with <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>A</mi><mi>D</mi></msub></mrow></semantics></math></inline-formula> = 0.01 and <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>M</mi><mrow><mi>S</mi><mi>T</mi></mrow></msub></mrow></semantics></math></inline-formula> = 14.75°, as compared to the reference airfoil. Similarly, the lift coefficients for two other cases, where <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>A</mi><mi>D</mi></msub></mrow></semantics></math></inline-formula> = 0.05 and <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>A</mi><mi>D</mi></msub></mrow></semantics></math></inline-formula> = 0.0075, increased by 10.67% and 11.46%, respectively, compared to the reference airfoil. Furthermore, it was shown that the downward deflection of the leading edge increased the stall angle of attack and the nose-down pitching moment. Finally, it was concluded that the new radius of curvature of the DMLE airfoil minimized the streamwise adverse pressure gradient and prevented significant flow separation by delaying the Dynamic Stall Vortex (DSV) occurrence. |
| first_indexed | 2024-03-11T06:52:35Z |
| format | Article |
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| institution | Directory Open Access Journal |
| issn | 2313-7673 |
| language | English |
| last_indexed | 2024-03-11T06:52:35Z |
| publishDate | 2023-01-01 |
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| series | Biomimetics |
| spelling | doaj.art-6facf33ad98647fbbfa2c50fb0a6f86e2023-11-17T09:49:35ZengMDPI AGBiomimetics2313-76732023-01-01815110.3390/biomimetics8010051Flow Control around the UAS-S45 Pitching Airfoil Using a Dynamically Morphing Leading Edge (DMLE): A Numerical StudyMusavir Bashir0Nicola Zonzini1Ruxandra Mihaela Botez2Alessandro Ceruti3Tony Wong4Research Laboratory in Active Controls, Avionics and Aeroservoelasticity (LARCASE), Department of Systems Engineering, École de Technolgie Supérieure, 1100 Notre-Dame West, Montreal, QC H3C 1K3, CanadaDepartment of Industrial Engineering, University of Bologna, Via Zamboni, 33, 40126 Bologna, ItalyResearch Laboratory in Active Controls, Avionics and Aeroservoelasticity (LARCASE), Department of Systems Engineering, École de Technolgie Supérieure, 1100 Notre-Dame West, Montreal, QC H3C 1K3, CanadaDepartment of Industrial Engineering, University of Bologna, Via Zamboni, 33, 40126 Bologna, ItalyResearch Laboratory in Active Controls, Avionics and Aeroservoelasticity (LARCASE), Department of Systems Engineering, École de Technolgie Supérieure, 1100 Notre-Dame West, Montreal, QC H3C 1K3, CanadaThis paper investigates the effect of the Dynamically Morphing Leading Edge (DMLE) on the flow structure and the behavior of dynamic stall vortices around a pitching UAS-S45 airfoil with the objective of controlling the dynamic stall. An unsteady parametrization framework was developed to model the time-varying motion of the leading edge. This scheme was then integrated within the Ansys-Fluent numerical solver by developing a User-Defined-Function (UDF), with the aim to dynamically deflect the airfoil boundaries, and to control the dynamic mesh used to morph and to further adapt it. The dynamic and sliding mesh techniques were used to simulate the unsteady flow around the sinusoidally pitching UAS-S45 airfoil. While the <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>γ</mi><mo>−</mo><mi>R</mi><msub><mi>e</mi><mrow><mi>θ</mi><mo> </mo></mrow></msub></mrow></semantics></math></inline-formula> turbulence model adequately captured the flow structures of dynamic airfoils associated with leading-edge vortex formations for a wide range of Reynolds numbers, two broader studies are here considered. Firstly, (i) an oscillating airfoil with the DMLE is investigated; the pitching-oscillation motion of an airfoil and its parameters are defined, such as the droop nose amplitude (<inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>A</mi><mi>D</mi></msub></mrow></semantics></math></inline-formula>) and the pitch angle at which the leading-edge morphing starts (<inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>M</mi><mrow><mi>S</mi><mi>T</mi></mrow></msub></mrow></semantics></math></inline-formula>). The effects of the <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>A</mi><mi>D</mi></msub></mrow></semantics></math></inline-formula> and the <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>M</mi><mrow><mi>S</mi><mi>T</mi></mrow></msub></mrow></semantics></math></inline-formula> on the aerodynamic performance was studied, and three different amplitude cases are considered. Secondly, (ii) the DMLE of an airfoil motion at stall angles of attack was investigated. In this case, the airfoil was set at stall angles of attack rather than oscillating it. This study will provide the transient lift and drag at different deflection frequencies of 0.5 Hz, 1 Hz, 2 Hz, 5 Hz, and 10 Hz. The results showed that the lift coefficient for the airfoil increased by 20.15%, while a 16.58% delay in the dynamic stall angle was obtained for an oscillating airfoil with DMLE with <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>A</mi><mi>D</mi></msub></mrow></semantics></math></inline-formula> = 0.01 and <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>M</mi><mrow><mi>S</mi><mi>T</mi></mrow></msub></mrow></semantics></math></inline-formula> = 14.75°, as compared to the reference airfoil. Similarly, the lift coefficients for two other cases, where <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>A</mi><mi>D</mi></msub></mrow></semantics></math></inline-formula> = 0.05 and <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>A</mi><mi>D</mi></msub></mrow></semantics></math></inline-formula> = 0.0075, increased by 10.67% and 11.46%, respectively, compared to the reference airfoil. Furthermore, it was shown that the downward deflection of the leading edge increased the stall angle of attack and the nose-down pitching moment. Finally, it was concluded that the new radius of curvature of the DMLE airfoil minimized the streamwise adverse pressure gradient and prevented significant flow separation by delaying the Dynamic Stall Vortex (DSV) occurrence.https://www.mdpi.com/2313-7673/8/1/51morphingunsteady parameterizationDynamically Morphing Leading Edge (DMLE)dynamic stallflow control |
| spellingShingle | Musavir Bashir Nicola Zonzini Ruxandra Mihaela Botez Alessandro Ceruti Tony Wong Flow Control around the UAS-S45 Pitching Airfoil Using a Dynamically Morphing Leading Edge (DMLE): A Numerical Study Biomimetics morphing unsteady parameterization Dynamically Morphing Leading Edge (DMLE) dynamic stall flow control |
| title | Flow Control around the UAS-S45 Pitching Airfoil Using a Dynamically Morphing Leading Edge (DMLE): A Numerical Study |
| title_full | Flow Control around the UAS-S45 Pitching Airfoil Using a Dynamically Morphing Leading Edge (DMLE): A Numerical Study |
| title_fullStr | Flow Control around the UAS-S45 Pitching Airfoil Using a Dynamically Morphing Leading Edge (DMLE): A Numerical Study |
| title_full_unstemmed | Flow Control around the UAS-S45 Pitching Airfoil Using a Dynamically Morphing Leading Edge (DMLE): A Numerical Study |
| title_short | Flow Control around the UAS-S45 Pitching Airfoil Using a Dynamically Morphing Leading Edge (DMLE): A Numerical Study |
| title_sort | flow control around the uas s45 pitching airfoil using a dynamically morphing leading edge dmle a numerical study |
| topic | morphing unsteady parameterization Dynamically Morphing Leading Edge (DMLE) dynamic stall flow control |
| url | https://www.mdpi.com/2313-7673/8/1/51 |
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