Inflatable Leading Edge-Based Dynamic Stall Control considering Fluid-Structure Interaction
The inflatable leading edge (ILE) is explored as a dynamic stall control concept. A fluid-structure interaction (FSI) numerical method for the elastic membrane structure is constructed based on unsteady Reynolds-averaged Navier-Stokes (URANS) and a mass-spring-damper (MSD) structural dynamic model....
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| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
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Wiley
2020-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2020/9046542 |
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| author | Shi-Long Xing He-Yong Xu Ming-Sheng Ma Zheng-Yin Ye |
| author_facet | Shi-Long Xing He-Yong Xu Ming-Sheng Ma Zheng-Yin Ye |
| author_sort | Shi-Long Xing |
| collection | DOAJ |
| description | The inflatable leading edge (ILE) is explored as a dynamic stall control concept. A fluid-structure interaction (FSI) numerical method for the elastic membrane structure is constructed based on unsteady Reynolds-averaged Navier-Stokes (URANS) and a mass-spring-damper (MSD) structural dynamic model. Radial basis function- (RBF-) based mesh deformation algorithm and Laplacian and optimization-based mesh smoothing algorithm are adopted in flowfield simulations to achieve the pitching oscillation of the airfoil and to ensure the mesh quality. An airfoil is considered at a freestream Mach number of 0.3 and chord-based Reynolds number of 3.92×106. The airfoil is pitched about its quarter-chord axis at a sinusoidal motion. The numerical results indicate that the ILE can change the radius of curvature of the airfoil leading edge, which could reduce the streamwise adverse pressure gradient and suppress the formation of dynamic stall vortex (DSV). Although the maximum lift coefficient of the airfoil is slightly reduced during the control process, the maximum drag and pitching moment coefficients of the airfoil are greatly reduced by up to 66% and 75.2%, respectively. The relative position of the ILE has a significant influence on its control effect. The control laws of inflation and deflation also affect the control ability of the ILE. |
| format | Article |
| id | doaj-art-d7304a1271524a358c02f6a6fef0dde8 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2020-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-d7304a1271524a358c02f6a6fef0dde82025-02-03T06:46:17ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742020-01-01202010.1155/2020/90465429046542Inflatable Leading Edge-Based Dynamic Stall Control considering Fluid-Structure InteractionShi-Long Xing0He-Yong Xu1Ming-Sheng Ma2Zheng-Yin Ye3National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi’an, 710072, ChinaNational Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi’an, 710072, ChinaNational Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi’an, 710072, ChinaNational Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi’an, 710072, ChinaThe inflatable leading edge (ILE) is explored as a dynamic stall control concept. A fluid-structure interaction (FSI) numerical method for the elastic membrane structure is constructed based on unsteady Reynolds-averaged Navier-Stokes (URANS) and a mass-spring-damper (MSD) structural dynamic model. Radial basis function- (RBF-) based mesh deformation algorithm and Laplacian and optimization-based mesh smoothing algorithm are adopted in flowfield simulations to achieve the pitching oscillation of the airfoil and to ensure the mesh quality. An airfoil is considered at a freestream Mach number of 0.3 and chord-based Reynolds number of 3.92×106. The airfoil is pitched about its quarter-chord axis at a sinusoidal motion. The numerical results indicate that the ILE can change the radius of curvature of the airfoil leading edge, which could reduce the streamwise adverse pressure gradient and suppress the formation of dynamic stall vortex (DSV). Although the maximum lift coefficient of the airfoil is slightly reduced during the control process, the maximum drag and pitching moment coefficients of the airfoil are greatly reduced by up to 66% and 75.2%, respectively. The relative position of the ILE has a significant influence on its control effect. The control laws of inflation and deflation also affect the control ability of the ILE.http://dx.doi.org/10.1155/2020/9046542 |
| spellingShingle | Shi-Long Xing He-Yong Xu Ming-Sheng Ma Zheng-Yin Ye Inflatable Leading Edge-Based Dynamic Stall Control considering Fluid-Structure Interaction International Journal of Aerospace Engineering |
| title | Inflatable Leading Edge-Based Dynamic Stall Control considering Fluid-Structure Interaction |
| title_full | Inflatable Leading Edge-Based Dynamic Stall Control considering Fluid-Structure Interaction |
| title_fullStr | Inflatable Leading Edge-Based Dynamic Stall Control considering Fluid-Structure Interaction |
| title_full_unstemmed | Inflatable Leading Edge-Based Dynamic Stall Control considering Fluid-Structure Interaction |
| title_short | Inflatable Leading Edge-Based Dynamic Stall Control considering Fluid-Structure Interaction |
| title_sort | inflatable leading edge based dynamic stall control considering fluid structure interaction |
| url | http://dx.doi.org/10.1155/2020/9046542 |
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