ISBN: 9783832289768
ID: 9783832289768
Noise generated by high-lift devices is an essential part of the emitted sound of an airplane especially during approach when the engines run almost in idle conditions. The sound spectra are characterized by a mix of tonal and broadband components which are originated by the turbulent flow field, i.e., the noise generation is dominated by vortex-vortex and vortexwall interaction. Therefore, in the present study the turbulent flow field over a slat-main wing configuration is investigated by a large-eddy simulation (LES) and subsequently, the obtained unsteady flow data is used to analyze the acoustic field based on the acoustic perturbation equations (APE). The computations are performed at a freestream MACH number of Ma=0.16 at an angle of attack of 13 deg. The REYNOLDS number which is based on the clean chord length and the freestream velocity is Re= 1.4x10 6 . It is shown that a pure LES is not suitable for industrial applications when high REYNOLDS numbers are considered due to the vast required computational effort. Therefore, in the present work a zonal method is developed and implemented which combines the Ravsorns-averaged NAVIER-STOKES (RANS) equations and the spatially filtered NAVIER-STOKES equations solved in a large-eddy simulation, i.e., in regions where unsteady turbulent flow data is required an LES is performed whereas the remaining flow field regions are computed by a RANS simulation which is in terms of computational effort more efficient than an LES. First, the zonal RANS/LES method is validated by turbulent channel flow simulations and, second, it is applied to the slat-main wing configuration. Local Large-Eddy Simulation of a Slat-Wing Configuration: Noise generated by high-lift devices is an essential part of the emitted sound of an airplane especially during approach when the engines run almost in idle conditions. The sound spectra are characterized by a mix of tonal and broadband components which are originated by the turbulent flow field, i.e., the noise generation is dominated by vortex-vortex and vortexwall interaction. Therefore, in the present study the turbulent flow field over a slat-main wing configuration is investigated by a large-eddy simulation (LES) and subsequently, the obtained unsteady flow data is used to analyze the acoustic field based on the acoustic perturbation equations (APE). The computations are performed at a freestream MACH number of Ma=0.16 at an angle of attack of 13 deg. The REYNOLDS number which is based on the clean chord length and the freestream velocity is Re= 1.4x10 6 . It is shown that a pure LES is not suitable for industrial applications when high REYNOLDS numbers are considered due to the vast required computational effort. Therefore, in the present work a zonal method is developed and implemented which combines the Ravsorns-averaged NAVIER-STOKES (RANS) equations and the spatially filtered NAVIER-STOKES equations solved in a large-eddy simulation, i.e., in regions where unsteady turbulent flow data is required an LES is performed whereas the remaining flow field regions are computed by a RANS simulation which is in terms of computational effort more efficient than an LES. First, the zonal RANS/LES method is validated by turbulent channel flow simulations and, second, it is applied to the slat-main wing configuration., Shaker Verlag
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ISBN: 9783832289768
[ED: Buch], [PU: Shaker Verlag], Neuware - Noise generated by high-lift devices is an essential part of the emitted sound of an airplane especially during approach when the engines run almost in idle conditions. The sound spectra are characterized by a mix of tonal and broadband components which are originated by the turbulent flow field, i.e., the noise generation is dominated by vortex-vortex and vortexwall interaction. Therefore, in the present study the turbulent flow field over a slat-main wing configuration is investigated by a large-eddy simulation (LES) and subsequently, the obtained unsteady flow data is used to analyze the acoustic field based on the acoustic perturbation equations (APE). The computations are performed at a freestream MACH number of Ma=0.16 at an angle of attack of 13 deg. The REYNOLDS number which is based on the clean chord length and the freestream velocity is Re= 1.4x10 6 . It is shown that a pure LES is not suitable for industrial applications when high REYNOLDS numbers are considered due to the vast required computational effort. Therefore, in the present work a zonal method is developed and implemented which combines the Ravsorns-averaged NAVIER-STOKES (RANS) equations and the spatially filtered NAVIER-STOKES equations solved in a large-eddy simulation, i.e., in regions where unsteady turbulent flow data is required an LES is performed whereas the remaining flow field regions are computed by a RANS simulation which is in terms of computational effort more efficient than an LES. First, the zonal RANS/LES method is validated by turbulent channel flow simulations and, second, it is applied to the slat-main wing configuration., [SC: 0.00], Neuware, gewerbliches Angebot, 21x14.8x cm, [GW: 185g]
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2010
ISBN: 3832289763
ID: 18444685779
[EAN: 9783832289768], Neubuch, [PU: Shaker Verlag Mrz 2010], Neuware - Noise generated by high-lift devices is an essential part of the emitted sound of an airplane especially during approach when the engines run almost in idle conditions. The sound spectra are characterized by a mix of tonal and broadband components which are originated by the turbulent flow field, i.e., the noise generation is dominated by vortex-vortex and vortexwall interaction. Therefore, in the present study the turbulent flow field over a slat-main wing configuration is investigated by a large-eddy simulation (LES) and subsequently, the obtained unsteady flow data is used to analyze the acoustic field based on the acoustic perturbation equations (APE). The computations are performed at a freestream MACH number of Ma=0.16 at an angle of attack of 13 deg. The REYNOLDS number which is based on the clean chord length and the freestream velocity is Re= 1.4x10 6 . It is shown that a pure LES is not suitable for industrial applications when high REYNOLDS numbers are considered due to the vast required computational effort. Therefore, in the present work a zonal method is developed and implemented which combines the Ravsorns-averaged NAVIER-STOKES (RANS) equations and the spatially filtered NAVIER-STOKES equations solved in a large-eddy simulation, i.e., in regions where unsteady turbulent flow data is required an LES is performed whereas the remaining flow field regions are computed by a RANS simulation which is in terms of computational effort more efficient than an LES. First, the zonal RANS/LES method is validated by turbulent channel flow simulations and, second, it is applied to the slat-main wing configuration. 123 pp. Englisch
Abebooks.de
Buchhandlung - Bides GbR, Dresden, Germany [52676528] [Rating: 5 (von 5)]
NEW BOOK Versandkosten: EUR 9.29 Details... |
2010, ISBN: 3832289763
ID: 17022853305
[EAN: 9783832289768], Neubuch, [PU: Shaker Verlag Mrz 2010], Neuware - Noise generated by high-lift devices is an essential part of the emitted sound of an airplane especially during approach when the engines run almost in idle conditions. The sound spectra are characterized by a mix of tonal and broadband components which are originated by the turbulent flow field, i.e., the noise generation is dominated by vortex-vortex and vortexwall interaction. Therefore, in the present study the turbulent flow field over a slat-main wing configuration is investigated by a large-eddy simulation (LES) and subsequently, the obtained unsteady flow data is used to analyze the acoustic field based on the acoustic perturbation equations (APE). The computations are performed at a freestream MACH number of Ma=0.16 at an angle of attack of 13 deg. The REYNOLDS number which is based on the clean chord length and the freestream velocity is Re= 1.4x10 6 . It is shown that a pure LES is not suitable for industrial applications when high REYNOLDS numbers are considered due to the vast required computational effort. Therefore, in the present work a zonal method is developed and implemented which combines the Ravsorns-averaged NAVIER-STOKES (RANS) equations and the spatially filtered NAVIER-STOKES equations solved in a large-eddy simulation, i.e., in regions where unsteady turbulent flow data is required an LES is performed whereas the remaining flow field regions are computed by a RANS simulation which is in terms of computational effort more efficient than an LES. First, the zonal RANS/LES method is validated by turbulent channel flow simulations and, second, it is applied to the slat-main wing configuration. 123 pp. Englisch
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Rhein-Team Lörrach Ivano Narducci e.K., Lörrach, Germany [57451429] [Rating: 5 (von 5)]
NEW BOOK Versandkosten: EUR 5.41 Details... |
2010, ISBN: 3832289763
ID: 17021811806
[EAN: 9783832289768], Neubuch, [PU: Shaker Verlag Mrz 2010], Neuware - Noise generated by high-lift devices is an essential part of the emitted sound of an airplane especially during approach when the engines run almost in idle conditions. The sound spectra are characterized by a mix of tonal and broadband components which are originated by the turbulent flow field, i.e., the noise generation is dominated by vortex-vortex and vortexwall interaction. Therefore, in the present study the turbulent flow field over a slat-main wing configuration is investigated by a large-eddy simulation (LES) and subsequently, the obtained unsteady flow data is used to analyze the acoustic field based on the acoustic perturbation equations (APE). The computations are performed at a freestream MACH number of Ma=0.16 at an angle of attack of 13 deg. The REYNOLDS number which is based on the clean chord length and the freestream velocity is Re= 1.4x10 6 . It is shown that a pure LES is not suitable for industrial applications when high REYNOLDS numbers are considered due to the vast required computational effort. Therefore, in the present work a zonal method is developed and implemented which combines the Ravsorns-averaged NAVIER-STOKES (RANS) equations and the spatially filtered NAVIER-STOKES equations solved in a large-eddy simulation, i.e., in regions where unsteady turbulent flow data is required an LES is performed whereas the remaining flow field regions are computed by a RANS simulation which is in terms of computational effort more efficient than an LES. First, the zonal RANS/LES method is validated by turbulent channel flow simulations and, second, it is applied to the slat-main wing configuration. 123 pp. Englisch
Abebooks.de
Rheinberg-Buch, Bergisch Gladbach, Germany [53870650] [Rating: 5 (von 5)]
NEW BOOK Versandkosten: EUR 10.82 Details... |
Autor: | |
Titel: | Local Large-Eddy Simulation of a Slat-Wing Configuration. |
ISBN-Nummer: | 9783832289768 |
Detailangaben zum Buch - Local Large-Eddy Simulation of a Slat-Wing Configuration.
EAN (ISBN-13): 9783832289768
ISBN (ISBN-10): 3832289763
Taschenbuch
Erscheinungsjahr: 2010
Herausgeber: Aachen : Shaker
Buch in der Datenbank seit 23.05.2012 10:53:50
Buch zuletzt gefunden am 01.07.2016 15:13:01
ISBN/EAN: 9783832289768
ISBN - alternative Schreibweisen:
3-8322-8976-3, 978-3-8322-8976-8
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