Aeroacoustic Design Optimization and Experimental Investigation of Sawtooth Trailing-Edges for Maximized Noise Reduction
Purpose The aim of the current study is to employ a formal optimization approach and to find the optimal sawtooth shape of trailing-edge serrations that maximize the turbulent boundary layer-trailing edge (TBL-TE) interaction noise reduction. Methods Lyu's semi-empirical model is used for the o...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Al Tlua, Basim [verfasserIn] |
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| Format: |
E-Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
2022 |
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| Schlagwörter: |
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| Anmerkung: |
© Krishtel eMaging Solutions Private Limited 2022 |
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| Übergeordnetes Werk: |
Enthalten in: Journal of vibration engineering & technologies - Singapore : Springer Singapore, 2018, 11(2022), 2 vom: 21. Juni, Seite 563-575 |
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| Übergeordnetes Werk: |
volume:11 ; year:2022 ; number:2 ; day:21 ; month:06 ; pages:563-575 |
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| DOI / URN: |
10.1007/s42417-022-00594-w |
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| Katalog-ID: |
SPR049861522 |
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| 520 | |a Purpose The aim of the current study is to employ a formal optimization approach and to find the optimal sawtooth shape of trailing-edge serrations that maximize the turbulent boundary layer-trailing edge (TBL-TE) interaction noise reduction. Methods Lyu's semi-empirical model is used for the optimization approach to investigate a semi-infinite flat plate at zero angle of attack (AoA) and low Mach Number. The ability of sawtooth trailing-edge serrations to reduce TBL-TE noise is analyzed through a single-objective numerical optimization study and trailing-edges tested in a wind tunnel. Four different cases of sawtooth serration geometries are tested for NACA-0012 airfoil and flat-plate trailing edges. Results Results from the optimization study are used to examine and validate the influence of serration design parameters. For all the cases, the optimum size shows that the maximum noise reduction is located in regions of the design space where the amplitude is maximal, and the wavelength is minimal. Moreover, based on the optimization analyses, the Saw-1 serration provides the greatest noise reduction up to 12.89 dB over a wider range of frequencies. Experimental and optimization results are then compared. Conclusion It is concluded that numerical and experimental results agree that optimized sawtooth trailing-edge configurations can yield less TBL-TE noise compared to the traditional straight-trailing-edge configuration. The optimization studies underestimated the measurements by about 2 to 12 dB, but the tendency between the different serration geometries was predicted correctly. | ||
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| 650 | 4 | |a Trailing edge serrations |7 (dpeaa)DE-He213 | |
| 650 | 4 | |a Aircraft noise |7 (dpeaa)DE-He213 | |
| 650 | 4 | |a Noise reduction |7 (dpeaa)DE-He213 | |
| 700 | 1 | |a Rocha, Joana |0 (orcid)0000-0003-4184-5096 |4 aut | |
| 773 | 0 | 8 | |i Enthalten in |t Journal of vibration engineering & technologies |d Singapore : Springer Singapore, 2018 |g 11(2022), 2 vom: 21. Juni, Seite 563-575 |w (DE-627)1030123837 |w (DE-600)2941414-3 |x 2523-3939 |7 nnns |
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10.1007/s42417-022-00594-w doi (DE-627)SPR049861522 (SPR)s42417-022-00594-w-e DE-627 ger DE-627 rakwb eng Al Tlua, Basim verfasserin aut Aeroacoustic Design Optimization and Experimental Investigation of Sawtooth Trailing-Edges for Maximized Noise Reduction 2022 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Krishtel eMaging Solutions Private Limited 2022 Purpose The aim of the current study is to employ a formal optimization approach and to find the optimal sawtooth shape of trailing-edge serrations that maximize the turbulent boundary layer-trailing edge (TBL-TE) interaction noise reduction. Methods Lyu's semi-empirical model is used for the optimization approach to investigate a semi-infinite flat plate at zero angle of attack (AoA) and low Mach Number. The ability of sawtooth trailing-edge serrations to reduce TBL-TE noise is analyzed through a single-objective numerical optimization study and trailing-edges tested in a wind tunnel. Four different cases of sawtooth serration geometries are tested for NACA-0012 airfoil and flat-plate trailing edges. Results Results from the optimization study are used to examine and validate the influence of serration design parameters. For all the cases, the optimum size shows that the maximum noise reduction is located in regions of the design space where the amplitude is maximal, and the wavelength is minimal. Moreover, based on the optimization analyses, the Saw-1 serration provides the greatest noise reduction up to 12.89 dB over a wider range of frequencies. Experimental and optimization results are then compared. Conclusion It is concluded that numerical and experimental results agree that optimized sawtooth trailing-edge configurations can yield less TBL-TE noise compared to the traditional straight-trailing-edge configuration. The optimization studies underestimated the measurements by about 2 to 12 dB, but the tendency between the different serration geometries was predicted correctly. Design optimization (dpeaa)DE-He213 Trailing edge serrations (dpeaa)DE-He213 Aircraft noise (dpeaa)DE-He213 Noise reduction (dpeaa)DE-He213 Rocha, Joana (orcid)0000-0003-4184-5096 aut Enthalten in Journal of vibration engineering & technologies Singapore : Springer Singapore, 2018 11(2022), 2 vom: 21. Juni, Seite 563-575 (DE-627)1030123837 (DE-600)2941414-3 2523-3939 nnns volume:11 year:2022 number:2 day:21 month:06 pages:563-575 https://dx.doi.org/10.1007/s42417-022-00594-w lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4328 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 11 2022 2 21 06 563-575 |
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10.1007/s42417-022-00594-w doi (DE-627)SPR049861522 (SPR)s42417-022-00594-w-e DE-627 ger DE-627 rakwb eng Al Tlua, Basim verfasserin aut Aeroacoustic Design Optimization and Experimental Investigation of Sawtooth Trailing-Edges for Maximized Noise Reduction 2022 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Krishtel eMaging Solutions Private Limited 2022 Purpose The aim of the current study is to employ a formal optimization approach and to find the optimal sawtooth shape of trailing-edge serrations that maximize the turbulent boundary layer-trailing edge (TBL-TE) interaction noise reduction. Methods Lyu's semi-empirical model is used for the optimization approach to investigate a semi-infinite flat plate at zero angle of attack (AoA) and low Mach Number. The ability of sawtooth trailing-edge serrations to reduce TBL-TE noise is analyzed through a single-objective numerical optimization study and trailing-edges tested in a wind tunnel. Four different cases of sawtooth serration geometries are tested for NACA-0012 airfoil and flat-plate trailing edges. Results Results from the optimization study are used to examine and validate the influence of serration design parameters. For all the cases, the optimum size shows that the maximum noise reduction is located in regions of the design space where the amplitude is maximal, and the wavelength is minimal. Moreover, based on the optimization analyses, the Saw-1 serration provides the greatest noise reduction up to 12.89 dB over a wider range of frequencies. Experimental and optimization results are then compared. Conclusion It is concluded that numerical and experimental results agree that optimized sawtooth trailing-edge configurations can yield less TBL-TE noise compared to the traditional straight-trailing-edge configuration. The optimization studies underestimated the measurements by about 2 to 12 dB, but the tendency between the different serration geometries was predicted correctly. Design optimization (dpeaa)DE-He213 Trailing edge serrations (dpeaa)DE-He213 Aircraft noise (dpeaa)DE-He213 Noise reduction (dpeaa)DE-He213 Rocha, Joana (orcid)0000-0003-4184-5096 aut Enthalten in Journal of vibration engineering & technologies Singapore : Springer Singapore, 2018 11(2022), 2 vom: 21. Juni, Seite 563-575 (DE-627)1030123837 (DE-600)2941414-3 2523-3939 nnns volume:11 year:2022 number:2 day:21 month:06 pages:563-575 https://dx.doi.org/10.1007/s42417-022-00594-w lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4328 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 11 2022 2 21 06 563-575 |
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10.1007/s42417-022-00594-w doi (DE-627)SPR049861522 (SPR)s42417-022-00594-w-e DE-627 ger DE-627 rakwb eng Al Tlua, Basim verfasserin aut Aeroacoustic Design Optimization and Experimental Investigation of Sawtooth Trailing-Edges for Maximized Noise Reduction 2022 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Krishtel eMaging Solutions Private Limited 2022 Purpose The aim of the current study is to employ a formal optimization approach and to find the optimal sawtooth shape of trailing-edge serrations that maximize the turbulent boundary layer-trailing edge (TBL-TE) interaction noise reduction. Methods Lyu's semi-empirical model is used for the optimization approach to investigate a semi-infinite flat plate at zero angle of attack (AoA) and low Mach Number. The ability of sawtooth trailing-edge serrations to reduce TBL-TE noise is analyzed through a single-objective numerical optimization study and trailing-edges tested in a wind tunnel. Four different cases of sawtooth serration geometries are tested for NACA-0012 airfoil and flat-plate trailing edges. Results Results from the optimization study are used to examine and validate the influence of serration design parameters. For all the cases, the optimum size shows that the maximum noise reduction is located in regions of the design space where the amplitude is maximal, and the wavelength is minimal. Moreover, based on the optimization analyses, the Saw-1 serration provides the greatest noise reduction up to 12.89 dB over a wider range of frequencies. Experimental and optimization results are then compared. Conclusion It is concluded that numerical and experimental results agree that optimized sawtooth trailing-edge configurations can yield less TBL-TE noise compared to the traditional straight-trailing-edge configuration. The optimization studies underestimated the measurements by about 2 to 12 dB, but the tendency between the different serration geometries was predicted correctly. Design optimization (dpeaa)DE-He213 Trailing edge serrations (dpeaa)DE-He213 Aircraft noise (dpeaa)DE-He213 Noise reduction (dpeaa)DE-He213 Rocha, Joana (orcid)0000-0003-4184-5096 aut Enthalten in Journal of vibration engineering & technologies Singapore : Springer Singapore, 2018 11(2022), 2 vom: 21. Juni, Seite 563-575 (DE-627)1030123837 (DE-600)2941414-3 2523-3939 nnns volume:11 year:2022 number:2 day:21 month:06 pages:563-575 https://dx.doi.org/10.1007/s42417-022-00594-w lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4328 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 11 2022 2 21 06 563-575 |
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10.1007/s42417-022-00594-w doi (DE-627)SPR049861522 (SPR)s42417-022-00594-w-e DE-627 ger DE-627 rakwb eng Al Tlua, Basim verfasserin aut Aeroacoustic Design Optimization and Experimental Investigation of Sawtooth Trailing-Edges for Maximized Noise Reduction 2022 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Krishtel eMaging Solutions Private Limited 2022 Purpose The aim of the current study is to employ a formal optimization approach and to find the optimal sawtooth shape of trailing-edge serrations that maximize the turbulent boundary layer-trailing edge (TBL-TE) interaction noise reduction. Methods Lyu's semi-empirical model is used for the optimization approach to investigate a semi-infinite flat plate at zero angle of attack (AoA) and low Mach Number. The ability of sawtooth trailing-edge serrations to reduce TBL-TE noise is analyzed through a single-objective numerical optimization study and trailing-edges tested in a wind tunnel. Four different cases of sawtooth serration geometries are tested for NACA-0012 airfoil and flat-plate trailing edges. Results Results from the optimization study are used to examine and validate the influence of serration design parameters. For all the cases, the optimum size shows that the maximum noise reduction is located in regions of the design space where the amplitude is maximal, and the wavelength is minimal. Moreover, based on the optimization analyses, the Saw-1 serration provides the greatest noise reduction up to 12.89 dB over a wider range of frequencies. Experimental and optimization results are then compared. Conclusion It is concluded that numerical and experimental results agree that optimized sawtooth trailing-edge configurations can yield less TBL-TE noise compared to the traditional straight-trailing-edge configuration. The optimization studies underestimated the measurements by about 2 to 12 dB, but the tendency between the different serration geometries was predicted correctly. Design optimization (dpeaa)DE-He213 Trailing edge serrations (dpeaa)DE-He213 Aircraft noise (dpeaa)DE-He213 Noise reduction (dpeaa)DE-He213 Rocha, Joana (orcid)0000-0003-4184-5096 aut Enthalten in Journal of vibration engineering & technologies Singapore : Springer Singapore, 2018 11(2022), 2 vom: 21. Juni, Seite 563-575 (DE-627)1030123837 (DE-600)2941414-3 2523-3939 nnns volume:11 year:2022 number:2 day:21 month:06 pages:563-575 https://dx.doi.org/10.1007/s42417-022-00594-w lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4328 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 11 2022 2 21 06 563-575 |
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10.1007/s42417-022-00594-w doi (DE-627)SPR049861522 (SPR)s42417-022-00594-w-e DE-627 ger DE-627 rakwb eng Al Tlua, Basim verfasserin aut Aeroacoustic Design Optimization and Experimental Investigation of Sawtooth Trailing-Edges for Maximized Noise Reduction 2022 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Krishtel eMaging Solutions Private Limited 2022 Purpose The aim of the current study is to employ a formal optimization approach and to find the optimal sawtooth shape of trailing-edge serrations that maximize the turbulent boundary layer-trailing edge (TBL-TE) interaction noise reduction. Methods Lyu's semi-empirical model is used for the optimization approach to investigate a semi-infinite flat plate at zero angle of attack (AoA) and low Mach Number. The ability of sawtooth trailing-edge serrations to reduce TBL-TE noise is analyzed through a single-objective numerical optimization study and trailing-edges tested in a wind tunnel. Four different cases of sawtooth serration geometries are tested for NACA-0012 airfoil and flat-plate trailing edges. Results Results from the optimization study are used to examine and validate the influence of serration design parameters. For all the cases, the optimum size shows that the maximum noise reduction is located in regions of the design space where the amplitude is maximal, and the wavelength is minimal. Moreover, based on the optimization analyses, the Saw-1 serration provides the greatest noise reduction up to 12.89 dB over a wider range of frequencies. Experimental and optimization results are then compared. Conclusion It is concluded that numerical and experimental results agree that optimized sawtooth trailing-edge configurations can yield less TBL-TE noise compared to the traditional straight-trailing-edge configuration. The optimization studies underestimated the measurements by about 2 to 12 dB, but the tendency between the different serration geometries was predicted correctly. Design optimization (dpeaa)DE-He213 Trailing edge serrations (dpeaa)DE-He213 Aircraft noise (dpeaa)DE-He213 Noise reduction (dpeaa)DE-He213 Rocha, Joana (orcid)0000-0003-4184-5096 aut Enthalten in Journal of vibration engineering & technologies Singapore : Springer Singapore, 2018 11(2022), 2 vom: 21. Juni, Seite 563-575 (DE-627)1030123837 (DE-600)2941414-3 2523-3939 nnns volume:11 year:2022 number:2 day:21 month:06 pages:563-575 https://dx.doi.org/10.1007/s42417-022-00594-w lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4328 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 11 2022 2 21 06 563-575 |
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<?xml version="1.0" encoding="UTF-8"?><collection xmlns="http://www.loc.gov/MARC21/slim"><record><leader>01000naa a22002652 4500</leader><controlfield tag="001">SPR049861522</controlfield><controlfield tag="003">DE-627</controlfield><controlfield tag="005">20230328064845.0</controlfield><controlfield tag="007">cr uuu---uuuuu</controlfield><controlfield tag="008">230328s2022 xx |||||o 00| ||eng c</controlfield><datafield tag="024" ind1="7" ind2=" "><subfield code="a">10.1007/s42417-022-00594-w</subfield><subfield code="2">doi</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(DE-627)SPR049861522</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(SPR)s42417-022-00594-w-e</subfield></datafield><datafield tag="040" ind1=" " ind2=" "><subfield code="a">DE-627</subfield><subfield code="b">ger</subfield><subfield code="c">DE-627</subfield><subfield code="e">rakwb</subfield></datafield><datafield tag="041" ind1=" " ind2=" "><subfield code="a">eng</subfield></datafield><datafield tag="100" ind1="1" ind2=" "><subfield code="a">Al Tlua, Basim</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="245" ind1="1" ind2="0"><subfield code="a">Aeroacoustic Design Optimization and Experimental Investigation of Sawtooth Trailing-Edges for Maximized Noise Reduction</subfield></datafield><datafield tag="264" ind1=" " ind2="1"><subfield code="c">2022</subfield></datafield><datafield tag="336" ind1=" " ind2=" "><subfield code="a">Text</subfield><subfield code="b">txt</subfield><subfield code="2">rdacontent</subfield></datafield><datafield tag="337" ind1=" " ind2=" "><subfield code="a">Computermedien</subfield><subfield code="b">c</subfield><subfield code="2">rdamedia</subfield></datafield><datafield tag="338" ind1=" " ind2=" "><subfield code="a">Online-Ressource</subfield><subfield code="b">cr</subfield><subfield code="2">rdacarrier</subfield></datafield><datafield tag="500" ind1=" " ind2=" "><subfield code="a">© Krishtel eMaging Solutions Private Limited 2022</subfield></datafield><datafield tag="520" ind1=" " ind2=" "><subfield code="a">Purpose The aim of the current study is to employ a formal optimization approach and to find the optimal sawtooth shape of trailing-edge serrations that maximize the turbulent boundary layer-trailing edge (TBL-TE) interaction noise reduction. Methods Lyu's semi-empirical model is used for the optimization approach to investigate a semi-infinite flat plate at zero angle of attack (AoA) and low Mach Number. The ability of sawtooth trailing-edge serrations to reduce TBL-TE noise is analyzed through a single-objective numerical optimization study and trailing-edges tested in a wind tunnel. Four different cases of sawtooth serration geometries are tested for NACA-0012 airfoil and flat-plate trailing edges. Results Results from the optimization study are used to examine and validate the influence of serration design parameters. For all the cases, the optimum size shows that the maximum noise reduction is located in regions of the design space where the amplitude is maximal, and the wavelength is minimal. Moreover, based on the optimization analyses, the Saw-1 serration provides the greatest noise reduction up to 12.89 dB over a wider range of frequencies. Experimental and optimization results are then compared. Conclusion It is concluded that numerical and experimental results agree that optimized sawtooth trailing-edge configurations can yield less TBL-TE noise compared to the traditional straight-trailing-edge configuration. 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Al Tlua, Basim |
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Al Tlua, Basim misc Design optimization misc Trailing edge serrations misc Aircraft noise misc Noise reduction Aeroacoustic Design Optimization and Experimental Investigation of Sawtooth Trailing-Edges for Maximized Noise Reduction |
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Aeroacoustic Design Optimization and Experimental Investigation of Sawtooth Trailing-Edges for Maximized Noise Reduction Design optimization (dpeaa)DE-He213 Trailing edge serrations (dpeaa)DE-He213 Aircraft noise (dpeaa)DE-He213 Noise reduction (dpeaa)DE-He213 |
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misc Design optimization misc Trailing edge serrations misc Aircraft noise misc Noise reduction |
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Aeroacoustic Design Optimization and Experimental Investigation of Sawtooth Trailing-Edges for Maximized Noise Reduction |
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aeroacoustic design optimization and experimental investigation of sawtooth trailing-edges for maximized noise reduction |
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Aeroacoustic Design Optimization and Experimental Investigation of Sawtooth Trailing-Edges for Maximized Noise Reduction |
| abstract |
Purpose The aim of the current study is to employ a formal optimization approach and to find the optimal sawtooth shape of trailing-edge serrations that maximize the turbulent boundary layer-trailing edge (TBL-TE) interaction noise reduction. Methods Lyu's semi-empirical model is used for the optimization approach to investigate a semi-infinite flat plate at zero angle of attack (AoA) and low Mach Number. The ability of sawtooth trailing-edge serrations to reduce TBL-TE noise is analyzed through a single-objective numerical optimization study and trailing-edges tested in a wind tunnel. Four different cases of sawtooth serration geometries are tested for NACA-0012 airfoil and flat-plate trailing edges. Results Results from the optimization study are used to examine and validate the influence of serration design parameters. For all the cases, the optimum size shows that the maximum noise reduction is located in regions of the design space where the amplitude is maximal, and the wavelength is minimal. Moreover, based on the optimization analyses, the Saw-1 serration provides the greatest noise reduction up to 12.89 dB over a wider range of frequencies. Experimental and optimization results are then compared. Conclusion It is concluded that numerical and experimental results agree that optimized sawtooth trailing-edge configurations can yield less TBL-TE noise compared to the traditional straight-trailing-edge configuration. The optimization studies underestimated the measurements by about 2 to 12 dB, but the tendency between the different serration geometries was predicted correctly. © Krishtel eMaging Solutions Private Limited 2022 |
| abstractGer |
Purpose The aim of the current study is to employ a formal optimization approach and to find the optimal sawtooth shape of trailing-edge serrations that maximize the turbulent boundary layer-trailing edge (TBL-TE) interaction noise reduction. Methods Lyu's semi-empirical model is used for the optimization approach to investigate a semi-infinite flat plate at zero angle of attack (AoA) and low Mach Number. The ability of sawtooth trailing-edge serrations to reduce TBL-TE noise is analyzed through a single-objective numerical optimization study and trailing-edges tested in a wind tunnel. Four different cases of sawtooth serration geometries are tested for NACA-0012 airfoil and flat-plate trailing edges. Results Results from the optimization study are used to examine and validate the influence of serration design parameters. For all the cases, the optimum size shows that the maximum noise reduction is located in regions of the design space where the amplitude is maximal, and the wavelength is minimal. Moreover, based on the optimization analyses, the Saw-1 serration provides the greatest noise reduction up to 12.89 dB over a wider range of frequencies. Experimental and optimization results are then compared. Conclusion It is concluded that numerical and experimental results agree that optimized sawtooth trailing-edge configurations can yield less TBL-TE noise compared to the traditional straight-trailing-edge configuration. The optimization studies underestimated the measurements by about 2 to 12 dB, but the tendency between the different serration geometries was predicted correctly. © Krishtel eMaging Solutions Private Limited 2022 |
| abstract_unstemmed |
Purpose The aim of the current study is to employ a formal optimization approach and to find the optimal sawtooth shape of trailing-edge serrations that maximize the turbulent boundary layer-trailing edge (TBL-TE) interaction noise reduction. Methods Lyu's semi-empirical model is used for the optimization approach to investigate a semi-infinite flat plate at zero angle of attack (AoA) and low Mach Number. The ability of sawtooth trailing-edge serrations to reduce TBL-TE noise is analyzed through a single-objective numerical optimization study and trailing-edges tested in a wind tunnel. Four different cases of sawtooth serration geometries are tested for NACA-0012 airfoil and flat-plate trailing edges. Results Results from the optimization study are used to examine and validate the influence of serration design parameters. For all the cases, the optimum size shows that the maximum noise reduction is located in regions of the design space where the amplitude is maximal, and the wavelength is minimal. Moreover, based on the optimization analyses, the Saw-1 serration provides the greatest noise reduction up to 12.89 dB over a wider range of frequencies. Experimental and optimization results are then compared. Conclusion It is concluded that numerical and experimental results agree that optimized sawtooth trailing-edge configurations can yield less TBL-TE noise compared to the traditional straight-trailing-edge configuration. The optimization studies underestimated the measurements by about 2 to 12 dB, but the tendency between the different serration geometries was predicted correctly. © Krishtel eMaging Solutions Private Limited 2022 |
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Aeroacoustic Design Optimization and Experimental Investigation of Sawtooth Trailing-Edges for Maximized Noise Reduction |
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Rocha, Joana |
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Methods Lyu's semi-empirical model is used for the optimization approach to investigate a semi-infinite flat plate at zero angle of attack (AoA) and low Mach Number. The ability of sawtooth trailing-edge serrations to reduce TBL-TE noise is analyzed through a single-objective numerical optimization study and trailing-edges tested in a wind tunnel. Four different cases of sawtooth serration geometries are tested for NACA-0012 airfoil and flat-plate trailing edges. Results Results from the optimization study are used to examine and validate the influence of serration design parameters. For all the cases, the optimum size shows that the maximum noise reduction is located in regions of the design space where the amplitude is maximal, and the wavelength is minimal. Moreover, based on the optimization analyses, the Saw-1 serration provides the greatest noise reduction up to 12.89 dB over a wider range of frequencies. Experimental and optimization results are then compared. 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