Dynamic Stall Characteristics of a Pitching Swept Finite Aspect Ratio Wing
This research will investigate various swept wing models, designing the mechanism for their pitching motion and control, designing wind tunnel implementation, and performing data measurements and analysis using particle image velocimetry. A NACA0012 section with an aspect ratio of AR = 4, free strea...
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ndltd-ndsu.edu-oai-library.ndsu.edu-10365-317212021-09-28T17:11:31Z Dynamic Stall Characteristics of a Pitching Swept Finite Aspect Ratio Wing Tomek, Kristopher airfoil dynamic pitching stall swept vortex This research will investigate various swept wing models, designing the mechanism for their pitching motion and control, designing wind tunnel implementation, and performing data measurements and analysis using particle image velocimetry. A NACA0012 section with an aspect ratio of AR = 4, free stream velocity of U∞=34 m/s, and Reynolds Number is Rec=2x105. Swept airfoils of Λ=0°, 15°, and 30° will be pitched sinusoidally between an AoA of 4°and 22°, at a reduced frequency of k=πfc/U∞=0.2. Higher sweep angles developing arch-type vortices interact with wing tip flow and abrupt tip stall is observed. Lower sweep angles possessed defined leading edge vortices persist near the tip after lift has collapsed at mid span. Stall angle was delayed during dynamic motion of the wing as well as the presence of arch and ring type vortices increased with sweep angle and contributed to flow reattachment along the top surface of the wing. 2021-01-15T16:25:49Z 2021-01-15T16:25:49Z 2019 text/thesis https://hdl.handle.net/10365/31721 NDSU policy 190.6.2 https://www.ndsu.edu/fileadmin/policy/190.pdf application/pdf North Dakota State University |
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airfoil dynamic pitching stall swept vortex |
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airfoil dynamic pitching stall swept vortex Tomek, Kristopher Dynamic Stall Characteristics of a Pitching Swept Finite Aspect Ratio Wing |
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This research will investigate various swept wing models, designing the mechanism for their pitching motion and control, designing wind tunnel implementation, and performing data measurements and analysis using particle image velocimetry. A NACA0012 section with an aspect ratio of AR = 4, free stream velocity of U∞=34 m/s, and Reynolds Number is Rec=2x105. Swept airfoils of Λ=0°, 15°, and 30° will be pitched sinusoidally between an AoA of 4°and 22°, at a reduced frequency of k=πfc/U∞=0.2. Higher sweep angles developing arch-type vortices interact with wing tip flow and abrupt tip stall is observed. Lower sweep angles possessed defined leading edge vortices persist near the tip after lift has collapsed at mid span. Stall angle was delayed during dynamic motion of the wing as well as the presence of arch and ring type vortices increased with sweep angle and contributed to flow reattachment along the top surface of the wing. |
author |
Tomek, Kristopher |
author_facet |
Tomek, Kristopher |
author_sort |
Tomek, Kristopher |
title |
Dynamic Stall Characteristics of a Pitching Swept Finite Aspect Ratio Wing |
title_short |
Dynamic Stall Characteristics of a Pitching Swept Finite Aspect Ratio Wing |
title_full |
Dynamic Stall Characteristics of a Pitching Swept Finite Aspect Ratio Wing |
title_fullStr |
Dynamic Stall Characteristics of a Pitching Swept Finite Aspect Ratio Wing |
title_full_unstemmed |
Dynamic Stall Characteristics of a Pitching Swept Finite Aspect Ratio Wing |
title_sort |
dynamic stall characteristics of a pitching swept finite aspect ratio wing |
publisher |
North Dakota State University |
publishDate |
2021 |
url |
https://hdl.handle.net/10365/31721 |
work_keys_str_mv |
AT tomekkristopher dynamicstallcharacteristicsofapitchingsweptfiniteaspectratiowing |
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1719485784780701696 |