Low order modeling of dynamic stall using vortex particle method and dynamic mode decomposition
Low order modelings are performed in this paper, including iterative Brinkman penalized vortex method (IBVM) and data-driven dynamic mode decomposition (DMD) for dynamic stall study of symmetric airfoil. The data are extracted from IBVM as input for flow field reconstruction using combinations of DM...
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| Veröffentlicht in: | International journal of micro air vehicles 2023-01, Vol.15 |
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| creator | Nguyen, Van Duc Duong, Viet Dung Trinh, Minh Hoang Nguyen, Hoang Quan Nguyen, Dang Thai Son |
| description | Low order modelings are performed in this paper, including iterative Brinkman penalized vortex method (IBVM) and data-driven dynamic mode decomposition (DMD) for dynamic stall study of symmetric airfoil. The data are extracted from IBVM as input for flow field reconstruction using combinations of DMD dominant modes, representing extracted flow features. The primary mode together with its harmonics, and the mean mode are termed to be dominant for the airfoil wake duplication at fixed angles of attack (
α
) ranging from
20
∘
to
90
∘
. For the dynamic stall duplication, at small and large pitching amplitudes, the nearfield and farfield vorticty contours from the DMD generally agree well with those from the IBVM. In addition, the lift coefficient from the DMD collapses well with that from the IBVM and the experiment. |
| doi_str_mv | 10.1177/17568293221147923 |
| format | Article |
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α
) ranging from
20
∘
to
90
∘
. For the dynamic stall duplication, at small and large pitching amplitudes, the nearfield and farfield vorticty contours from the DMD generally agree well with those from the IBVM. In addition, the lift coefficient from the DMD collapses well with that from the IBVM and the experiment.</description><identifier>ISSN: 1756-8293</identifier><identifier>EISSN: 1756-8307</identifier><identifier>DOI: 10.1177/17568293221147923</identifier><language>eng</language><publisher>London, England: SAGE Publications</publisher><subject>Aerodynamic coefficients ; Airfoils ; Angle of attack ; Decomposition ; Far fields ; Iterative methods ; Stalling</subject><ispartof>International journal of micro air vehicles, 2023-01, Vol.15</ispartof><rights>The Author(s) 2023</rights><rights>The Author(s) 2023. This work is licensed under the Creative Commons Attribution – Non-Commercial License https://creativecommons.org/licenses/by-nc/4.0/ (the “License”). Notwithstanding the ProQuest Terms and Conditions, you may use this content in accordance with the terms of the License.</rights><lds50>peer_reviewed</lds50><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed><cites>FETCH-LOGICAL-c307t-9ae6ac35935f441f292c334c4ce46c15e460a40fb630b0bcc5f826fec2deeb413</cites><orcidid>0000-0001-8734-6466 ; 0000-0001-5864-5555</orcidid></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktopdf>$$Uhttps://journals.sagepub.com/doi/pdf/10.1177/17568293221147923$$EPDF$$P50$$Gsage$$Hfree_for_read</linktopdf><linktohtml>$$Uhttps://journals.sagepub.com/doi/10.1177/17568293221147923$$EHTML$$P50$$Gsage$$Hfree_for_read</linktohtml><link.rule.ids>314,780,784,864,21966,27853,27924,27925,44945,45333</link.rule.ids></links><search><creatorcontrib>Nguyen, Van Duc</creatorcontrib><creatorcontrib>Duong, Viet Dung</creatorcontrib><creatorcontrib>Trinh, Minh Hoang</creatorcontrib><creatorcontrib>Nguyen, Hoang Quan</creatorcontrib><creatorcontrib>Nguyen, Dang Thai Son</creatorcontrib><title>Low order modeling of dynamic stall using vortex particle method and dynamic mode decomposition</title><title>International journal of micro air vehicles</title><description>Low order modelings are performed in this paper, including iterative Brinkman penalized vortex method (IBVM) and data-driven dynamic mode decomposition (DMD) for dynamic stall study of symmetric airfoil. The data are extracted from IBVM as input for flow field reconstruction using combinations of DMD dominant modes, representing extracted flow features. The primary mode together with its harmonics, and the mean mode are termed to be dominant for the airfoil wake duplication at fixed angles of attack (
α
) ranging from
20
∘
to
90
∘
. For the dynamic stall duplication, at small and large pitching amplitudes, the nearfield and farfield vorticty contours from the DMD generally agree well with those from the IBVM. 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The data are extracted from IBVM as input for flow field reconstruction using combinations of DMD dominant modes, representing extracted flow features. The primary mode together with its harmonics, and the mean mode are termed to be dominant for the airfoil wake duplication at fixed angles of attack (
α
) ranging from
20
∘
to
90
∘
. For the dynamic stall duplication, at small and large pitching amplitudes, the nearfield and farfield vorticty contours from the DMD generally agree well with those from the IBVM. In addition, the lift coefficient from the DMD collapses well with that from the IBVM and the experiment.</abstract><cop>London, England</cop><pub>SAGE Publications</pub><doi>10.1177/17568293221147923</doi><orcidid>https://orcid.org/0000-0001-8734-6466</orcidid><orcidid>https://orcid.org/0000-0001-5864-5555</orcidid><oa>free_for_read</oa></addata></record> |
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| subjects | Aerodynamic coefficients Airfoils Angle of attack Decomposition Far fields Iterative methods Stalling |
| title | Low order modeling of dynamic stall using vortex particle method and dynamic mode decomposition |
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