Study of Airfoil Deflections for Unsteady Aerodynamics Optimization in Pitching Airfoils
Camber deflection concepts for a VR-12 rotorcraft airfoil were studied for the optimization of unsteady aerodynamics, including dynamic stall conditions and wing–wing interactions during pitching. The designs are based on deflections of the leading edge and trailing edge sections of the airfoil. The...
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MDPI AG
2025-02-01
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| Series: | Applied Sciences |
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| Online Access: | https://www.mdpi.com/2076-3417/15/5/2455 |
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| author | William Refling Charles Fabijanic Thomas Sprengeler Yildirim Bora Suzen Jordi Estevadeordal |
| author_facet | William Refling Charles Fabijanic Thomas Sprengeler Yildirim Bora Suzen Jordi Estevadeordal |
| author_sort | William Refling |
| collection | DOAJ |
| description | Camber deflection concepts for a VR-12 rotorcraft airfoil were studied for the optimization of unsteady aerodynamics, including dynamic stall conditions and wing–wing interactions during pitching. The designs are based on deflections of the leading edge and trailing edge sections of the airfoil. The deflection parameters were initially established using Computational Fluid Dynamics (CFD). Results from CFD and Particle Image Velocimetry (PIV) were generated for various leading and trailing edge deflection combinations for comparison of their performances. The conditions of this study are for a Reynolds number of 250,000 and pitching reduced frequency of 0.04, representing a medium regime of rotorcraft operations. Linear tandem tests were performed to simulate unsteady wing–wing interactions. The effects of the deflections are discussed and compared to the baseline. Significant benefits are observed, notably dynamic stall mitigation from the leading edge (LE) deflected wing for certain angles of attack and decrease in the separation regions. Overall, from the numerical simulations and the experimental data fields, the LE deflection provides about 10% improvement, followed by the combined LE&TE deflections (8%). It is also found that combining various deflections can provide a performance increase over drastically different areas of the range of angle of attack. |
| format | Article |
| id | doaj-art-89b0a2be84b842fcbc51218544802dbc |
| institution | DOAJ |
| issn | 2076-3417 |
| language | English |
| publishDate | 2025-02-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Applied Sciences |
| spelling | doaj-art-89b0a2be84b842fcbc51218544802dbc2025-08-20T02:57:40ZengMDPI AGApplied Sciences2076-34172025-02-01155245510.3390/app15052455Study of Airfoil Deflections for Unsteady Aerodynamics Optimization in Pitching AirfoilsWilliam Refling0Charles Fabijanic1Thomas Sprengeler2Yildirim Bora Suzen3Jordi Estevadeordal4Department of Mechanical Engineering, North Dakota State University, Fargo, ND 58105, USADepartment of Mechanical Engineering, North Dakota State University, Fargo, ND 58105, USADepartment of Mechanical Engineering, North Dakota State University, Fargo, ND 58105, USADepartment of Mechanical Engineering, North Dakota State University, Fargo, ND 58105, USADepartment of Mechanical Engineering, North Dakota State University, Fargo, ND 58105, USACamber deflection concepts for a VR-12 rotorcraft airfoil were studied for the optimization of unsteady aerodynamics, including dynamic stall conditions and wing–wing interactions during pitching. The designs are based on deflections of the leading edge and trailing edge sections of the airfoil. The deflection parameters were initially established using Computational Fluid Dynamics (CFD). Results from CFD and Particle Image Velocimetry (PIV) were generated for various leading and trailing edge deflection combinations for comparison of their performances. The conditions of this study are for a Reynolds number of 250,000 and pitching reduced frequency of 0.04, representing a medium regime of rotorcraft operations. Linear tandem tests were performed to simulate unsteady wing–wing interactions. The effects of the deflections are discussed and compared to the baseline. Significant benefits are observed, notably dynamic stall mitigation from the leading edge (LE) deflected wing for certain angles of attack and decrease in the separation regions. Overall, from the numerical simulations and the experimental data fields, the LE deflection provides about 10% improvement, followed by the combined LE&TE deflections (8%). It is also found that combining various deflections can provide a performance increase over drastically different areas of the range of angle of attack.https://www.mdpi.com/2076-3417/15/5/2455airfoil aerodynamicspitching flow controlseparationdynamic stallparticle image velocimetrynumerical simulations |
| spellingShingle | William Refling Charles Fabijanic Thomas Sprengeler Yildirim Bora Suzen Jordi Estevadeordal Study of Airfoil Deflections for Unsteady Aerodynamics Optimization in Pitching Airfoils Applied Sciences airfoil aerodynamics pitching flow control separation dynamic stall particle image velocimetry numerical simulations |
| title | Study of Airfoil Deflections for Unsteady Aerodynamics Optimization in Pitching Airfoils |
| title_full | Study of Airfoil Deflections for Unsteady Aerodynamics Optimization in Pitching Airfoils |
| title_fullStr | Study of Airfoil Deflections for Unsteady Aerodynamics Optimization in Pitching Airfoils |
| title_full_unstemmed | Study of Airfoil Deflections for Unsteady Aerodynamics Optimization in Pitching Airfoils |
| title_short | Study of Airfoil Deflections for Unsteady Aerodynamics Optimization in Pitching Airfoils |
| title_sort | study of airfoil deflections for unsteady aerodynamics optimization in pitching airfoils |
| topic | airfoil aerodynamics pitching flow control separation dynamic stall particle image velocimetry numerical simulations |
| url | https://www.mdpi.com/2076-3417/15/5/2455 |
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