Effect of the wing trailing-edge flaps and spoilers position on the jet-vortex wake behind an aircraft during takeoff and landing run
The large-scale vortex structure of flow in the near wake behind an aircraft during its run on a runway is investigated numerically. The geometrical aircraft configuration was taken close to a mid-range commercial aircraft like Boeing 737-300. It included all essential elements: a body (fuselage), w...
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| Veröffentlicht in: | Proceedings of the Institution of Mechanical Engineers. Part G, Journal of aerospace engineering Journal of aerospace engineering, 2022-03, Vol.236 (3), p.490-501 |
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| container_title | Proceedings of the Institution of Mechanical Engineers. Part G, Journal of aerospace engineering |
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| creator | Tsirkunov, Yu M Lobanova, MA Tsvetkov, AI Schepanyuk, BA |
| description | The large-scale vortex structure of flow in the near wake behind an aircraft during its run on a runway is investigated numerically. The geometrical aircraft configuration was taken close to a mid-range commercial aircraft like Boeing 737-300. It included all essential elements: a body (fuselage), wings with winglets, horizontal and vertical stabilizers, engine nacelles, nacelle pylons, inboard flap track fairings, leading-edge and trailing-edge flaps, and spoilers. The position of flaps and spoilers corresponded to the takeoff and landing run conditions. Computational simulation was based on solving the Reynolds averaged Navier–Stokes equations closed with the Menter Shear Stress Transport turbulence model. Patterns of streamlines, fields of the axial vorticity and the turbulent intensity, vertical and horizontal velocity profiles in the wake are compared and discussed for both run regimes. The flow model was preliminary tested for validity by comparison of the calculated velocity profiles behind a reduced-scale aircraft model with those obtained in special wind tunnel experiments. |
| doi_str_mv | 10.1177/0954410019882150 |
| format | Article |
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The geometrical aircraft configuration was taken close to a mid-range commercial aircraft like Boeing 737-300. It included all essential elements: a body (fuselage), wings with winglets, horizontal and vertical stabilizers, engine nacelles, nacelle pylons, inboard flap track fairings, leading-edge and trailing-edge flaps, and spoilers. The position of flaps and spoilers corresponded to the takeoff and landing run conditions. Computational simulation was based on solving the Reynolds averaged Navier–Stokes equations closed with the Menter Shear Stress Transport turbulence model. Patterns of streamlines, fields of the axial vorticity and the turbulent intensity, vertical and horizontal velocity profiles in the wake are compared and discussed for both run regimes. The flow model was preliminary tested for validity by comparison of the calculated velocity profiles behind a reduced-scale aircraft model with those obtained in special wind tunnel experiments.</description><identifier>ISSN: 0954-4100</identifier><identifier>EISSN: 2041-3025</identifier><identifier>DOI: 10.1177/0954410019882150</identifier><language>eng</language><publisher>London, England: SAGE Publications</publisher><subject>Aircraft ; Aircraft configurations ; Aircraft landing ; Aircraft models ; Airframes ; Axial stress ; Commercial aircraft ; Fairings ; Fluid flow ; Fuselages ; Nacelles ; Pylons ; Shear stress ; Spoilers ; Stabilizers (fluid dynamics) ; Takeoff ; Trailing edge flaps ; Turbulence models ; Velocity distribution ; Vorticity ; Wind tunnel testing ; Wind tunnels ; Wings (aircraft)</subject><ispartof>Proceedings of the Institution of Mechanical Engineers. 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Part G, Journal of aerospace engineering</title><description>The large-scale vortex structure of flow in the near wake behind an aircraft during its run on a runway is investigated numerically. The geometrical aircraft configuration was taken close to a mid-range commercial aircraft like Boeing 737-300. It included all essential elements: a body (fuselage), wings with winglets, horizontal and vertical stabilizers, engine nacelles, nacelle pylons, inboard flap track fairings, leading-edge and trailing-edge flaps, and spoilers. The position of flaps and spoilers corresponded to the takeoff and landing run conditions. Computational simulation was based on solving the Reynolds averaged Navier–Stokes equations closed with the Menter Shear Stress Transport turbulence model. Patterns of streamlines, fields of the axial vorticity and the turbulent intensity, vertical and horizontal velocity profiles in the wake are compared and discussed for both run regimes. The flow model was preliminary tested for validity by comparison of the calculated velocity profiles behind a reduced-scale aircraft model with those obtained in special wind tunnel experiments.</description><subject>Aircraft</subject><subject>Aircraft configurations</subject><subject>Aircraft landing</subject><subject>Aircraft models</subject><subject>Airframes</subject><subject>Axial stress</subject><subject>Commercial aircraft</subject><subject>Fairings</subject><subject>Fluid flow</subject><subject>Fuselages</subject><subject>Nacelles</subject><subject>Pylons</subject><subject>Shear stress</subject><subject>Spoilers</subject><subject>Stabilizers (fluid dynamics)</subject><subject>Takeoff</subject><subject>Trailing edge flaps</subject><subject>Turbulence models</subject><subject>Velocity distribution</subject><subject>Vorticity</subject><subject>Wind tunnel testing</subject><subject>Wind tunnels</subject><subject>Wings (aircraft)</subject><issn>0954-4100</issn><issn>2041-3025</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2022</creationdate><recordtype>article</recordtype><recordid>eNp1UEtLxDAQDqLg-rh7DHiuJm3aJkdZ1gcseNFzSZPJbtba1CR19Qf4v013BUFwGGaG-R4Dg9AFJVeU1vU1ESVjlBAqOM9pSQ7QLCeMZgXJy0M0m-Bswo_RSQgbkqKsihn6WhgDKmJncFwD3tp-haOXtktDBnoF2HRyCFj2GofB2Q58wIMLNlrX45STagMxe3c-wgfeyhfALaxt4sseS-uVlyZiPfqddYKdMTu7LpVp58f-DB0Z2QU4_-mn6Pl28TS_z5aPdw_zm2Wm8iqPGWsVVwVnhnJNgBBZC6GNFpVqodS5rCXTlBhalznXChgXhQDDtTGsKjVpi1N0ufcdvHsbIcRm40bfp5NNXjHOhGB1nVhkz1LeheDBNIO3r9J_NpQ007Obv89OkmwvCXIFv6b_8r8BqfOAbw</recordid><startdate>20220301</startdate><enddate>20220301</enddate><creator>Tsirkunov, Yu M</creator><creator>Lobanova, MA</creator><creator>Tsvetkov, AI</creator><creator>Schepanyuk, BA</creator><general>SAGE Publications</general><general>SAGE PUBLICATIONS, INC</general><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>8FD</scope><scope>F28</scope><scope>FR3</scope><scope>H8D</scope><scope>L7M</scope><orcidid>https://orcid.org/0000-0002-5059-0446</orcidid></search><sort><creationdate>20220301</creationdate><title>Effect of the wing trailing-edge flaps and spoilers position on the jet-vortex wake behind an aircraft during takeoff and landing run</title><author>Tsirkunov, Yu M ; Lobanova, MA ; Tsvetkov, AI ; Schepanyuk, BA</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c262t-4bc8c384f18d0e00a799dfd96cbe5d2a7a4d10f17528dce48939ef8dff465d0b3</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2022</creationdate><topic>Aircraft</topic><topic>Aircraft configurations</topic><topic>Aircraft landing</topic><topic>Aircraft models</topic><topic>Airframes</topic><topic>Axial stress</topic><topic>Commercial aircraft</topic><topic>Fairings</topic><topic>Fluid flow</topic><topic>Fuselages</topic><topic>Nacelles</topic><topic>Pylons</topic><topic>Shear stress</topic><topic>Spoilers</topic><topic>Stabilizers (fluid dynamics)</topic><topic>Takeoff</topic><topic>Trailing edge flaps</topic><topic>Turbulence models</topic><topic>Velocity distribution</topic><topic>Vorticity</topic><topic>Wind tunnel testing</topic><topic>Wind tunnels</topic><topic>Wings (aircraft)</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Tsirkunov, Yu M</creatorcontrib><creatorcontrib>Lobanova, MA</creatorcontrib><creatorcontrib>Tsvetkov, AI</creatorcontrib><creatorcontrib>Schepanyuk, BA</creatorcontrib><collection>CrossRef</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>ANTE: Abstracts in New Technology & Engineering</collection><collection>Engineering Research Database</collection><collection>Aerospace Database</collection><collection>Advanced Technologies Database with Aerospace</collection><jtitle>Proceedings of the Institution of Mechanical Engineers. 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The geometrical aircraft configuration was taken close to a mid-range commercial aircraft like Boeing 737-300. It included all essential elements: a body (fuselage), wings with winglets, horizontal and vertical stabilizers, engine nacelles, nacelle pylons, inboard flap track fairings, leading-edge and trailing-edge flaps, and spoilers. The position of flaps and spoilers corresponded to the takeoff and landing run conditions. Computational simulation was based on solving the Reynolds averaged Navier–Stokes equations closed with the Menter Shear Stress Transport turbulence model. Patterns of streamlines, fields of the axial vorticity and the turbulent intensity, vertical and horizontal velocity profiles in the wake are compared and discussed for both run regimes. 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| ispartof | Proceedings of the Institution of Mechanical Engineers. Part G, Journal of aerospace engineering, 2022-03, Vol.236 (3), p.490-501 |
| issn | 0954-4100 2041-3025 |
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| source | SAGE Complete |
| subjects | Aircraft Aircraft configurations Aircraft landing Aircraft models Airframes Axial stress Commercial aircraft Fairings Fluid flow Fuselages Nacelles Pylons Shear stress Spoilers Stabilizers (fluid dynamics) Takeoff Trailing edge flaps Turbulence models Velocity distribution Vorticity Wind tunnel testing Wind tunnels Wings (aircraft) |
| title | Effect of the wing trailing-edge flaps and spoilers position on the jet-vortex wake behind an aircraft during takeoff and landing run |
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