Size effects of vane-type rectangular vortex generators installed on high-lift swept-back wing flap on lift force and flow fields
Abstract Vane-type vortex generators (VGs) are often installed on the flaps of high-lift systems of aircraft as retrofit devices for increasing the lift by suppressing flow separation. To reduce the number of VGs, increasing their heights is a viable solution for generating strong vortices. However,...
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| Autor*in: |
Ichikawa, Y. [verfasserIn] |
|---|
| Format: |
Artikel |
|---|---|
| Sprache: |
Englisch |
| Erschienen: |
2021 |
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| Anmerkung: |
© The Author(s), under exclusive licence to Springer-Verlag GmbH Germany, part of Springer Nature 2021 |
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| Übergeordnetes Werk: |
Enthalten in: Experiments in fluids - Springer Berlin Heidelberg, 1983, 62(2021), 8 vom: 12. Juli |
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| Übergeordnetes Werk: |
volume:62 ; year:2021 ; number:8 ; day:12 ; month:07 |
| Links: |
|---|
| DOI / URN: |
10.1007/s00348-021-03198-4 |
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| Katalog-ID: |
OLC2126583511 |
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| 520 | |a Abstract Vane-type vortex generators (VGs) are often installed on the flaps of high-lift systems of aircraft as retrofit devices for increasing the lift by suppressing flow separation. To reduce the number of VGs, increasing their heights is a viable solution for generating strong vortices. However, the maximum size of the VGs cannot be determined based on the available literature. We investigated the effect of size of a vane-type rectangular VG on the lift force of a half-span high-lift swept-back wing model. The experiments were performed in a low-speed wind tunnel at Reynolds number 1.86 × $ 10^{6} $. In this study, three different heights (Hv) of the VGs with co-rotating vortex configurations were tested, all of which were larger than the boundary layer thickness δ at the VG’s installation position of the flap. We observed that moderately sized VGs (Hv/δ = 4.8) maximized the increase in the lift coefficient, while excessively large VGs (Hv/δ = 9.6) reduced this increase. To examine this further, we measured the flow fields over the flap for VGs with both Hv/δ = 4.8 and 9.6 via stereoscopic particle image velocimetry. Results showed that VGs with Hv/δ = 9.6 generated a larger flow separation area as compared to that with Hv/δ = 4.8. For Hv/δ = 9.6, almost half of the vortex core interacted with the main wing wake; this implies that vortices generated by VGs with Hv/δ = 9.6 produce low-momentum fluid entrainment in the wake toward the boundary layer on the flap, thus diminishing the effect of the VGs. Graphic abstract | ||
| 700 | 1 | |a Koike, S. |4 aut | |
| 700 | 1 | |a Ito, Y. |4 aut | |
| 700 | 1 | |a Murayama, M. |4 aut | |
| 700 | 1 | |a Nakakita, K. |4 aut | |
| 700 | 1 | |a Yamamoto, K. |4 aut | |
| 700 | 1 | |a Kusunose, K. |4 aut | |
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10.1007/s00348-021-03198-4 doi (DE-627)OLC2126583511 (DE-He213)s00348-021-03198-4-p DE-627 ger DE-627 rakwb eng 620 530 VZ 530 VZ Ichikawa, Y. verfasserin aut Size effects of vane-type rectangular vortex generators installed on high-lift swept-back wing flap on lift force and flow fields 2021 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © The Author(s), under exclusive licence to Springer-Verlag GmbH Germany, part of Springer Nature 2021 Abstract Vane-type vortex generators (VGs) are often installed on the flaps of high-lift systems of aircraft as retrofit devices for increasing the lift by suppressing flow separation. To reduce the number of VGs, increasing their heights is a viable solution for generating strong vortices. However, the maximum size of the VGs cannot be determined based on the available literature. We investigated the effect of size of a vane-type rectangular VG on the lift force of a half-span high-lift swept-back wing model. The experiments were performed in a low-speed wind tunnel at Reynolds number 1.86 × $ 10^{6} $. In this study, three different heights (Hv) of the VGs with co-rotating vortex configurations were tested, all of which were larger than the boundary layer thickness δ at the VG’s installation position of the flap. We observed that moderately sized VGs (Hv/δ = 4.8) maximized the increase in the lift coefficient, while excessively large VGs (Hv/δ = 9.6) reduced this increase. To examine this further, we measured the flow fields over the flap for VGs with both Hv/δ = 4.8 and 9.6 via stereoscopic particle image velocimetry. Results showed that VGs with Hv/δ = 9.6 generated a larger flow separation area as compared to that with Hv/δ = 4.8. For Hv/δ = 9.6, almost half of the vortex core interacted with the main wing wake; this implies that vortices generated by VGs with Hv/δ = 9.6 produce low-momentum fluid entrainment in the wake toward the boundary layer on the flap, thus diminishing the effect of the VGs. Graphic abstract Koike, S. aut Ito, Y. aut Murayama, M. aut Nakakita, K. aut Yamamoto, K. aut Kusunose, K. aut Enthalten in Experiments in fluids Springer Berlin Heidelberg, 1983 62(2021), 8 vom: 12. Juli (DE-627)130443794 (DE-600)710083-8 (DE-576)015977404 0723-4864 nnns volume:62 year:2021 number:8 day:12 month:07 https://doi.org/10.1007/s00348-021-03198-4 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-PHY GBV_ILN_2018 GBV_ILN_4277 AR 62 2021 8 12 07 |
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10.1007/s00348-021-03198-4 doi (DE-627)OLC2126583511 (DE-He213)s00348-021-03198-4-p DE-627 ger DE-627 rakwb eng 620 530 VZ 530 VZ Ichikawa, Y. verfasserin aut Size effects of vane-type rectangular vortex generators installed on high-lift swept-back wing flap on lift force and flow fields 2021 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © The Author(s), under exclusive licence to Springer-Verlag GmbH Germany, part of Springer Nature 2021 Abstract Vane-type vortex generators (VGs) are often installed on the flaps of high-lift systems of aircraft as retrofit devices for increasing the lift by suppressing flow separation. To reduce the number of VGs, increasing their heights is a viable solution for generating strong vortices. However, the maximum size of the VGs cannot be determined based on the available literature. We investigated the effect of size of a vane-type rectangular VG on the lift force of a half-span high-lift swept-back wing model. The experiments were performed in a low-speed wind tunnel at Reynolds number 1.86 × $ 10^{6} $. In this study, three different heights (Hv) of the VGs with co-rotating vortex configurations were tested, all of which were larger than the boundary layer thickness δ at the VG’s installation position of the flap. We observed that moderately sized VGs (Hv/δ = 4.8) maximized the increase in the lift coefficient, while excessively large VGs (Hv/δ = 9.6) reduced this increase. To examine this further, we measured the flow fields over the flap for VGs with both Hv/δ = 4.8 and 9.6 via stereoscopic particle image velocimetry. Results showed that VGs with Hv/δ = 9.6 generated a larger flow separation area as compared to that with Hv/δ = 4.8. For Hv/δ = 9.6, almost half of the vortex core interacted with the main wing wake; this implies that vortices generated by VGs with Hv/δ = 9.6 produce low-momentum fluid entrainment in the wake toward the boundary layer on the flap, thus diminishing the effect of the VGs. Graphic abstract Koike, S. aut Ito, Y. aut Murayama, M. aut Nakakita, K. aut Yamamoto, K. aut Kusunose, K. aut Enthalten in Experiments in fluids Springer Berlin Heidelberg, 1983 62(2021), 8 vom: 12. Juli (DE-627)130443794 (DE-600)710083-8 (DE-576)015977404 0723-4864 nnns volume:62 year:2021 number:8 day:12 month:07 https://doi.org/10.1007/s00348-021-03198-4 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-PHY GBV_ILN_2018 GBV_ILN_4277 AR 62 2021 8 12 07 |
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10.1007/s00348-021-03198-4 doi (DE-627)OLC2126583511 (DE-He213)s00348-021-03198-4-p DE-627 ger DE-627 rakwb eng 620 530 VZ 530 VZ Ichikawa, Y. verfasserin aut Size effects of vane-type rectangular vortex generators installed on high-lift swept-back wing flap on lift force and flow fields 2021 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © The Author(s), under exclusive licence to Springer-Verlag GmbH Germany, part of Springer Nature 2021 Abstract Vane-type vortex generators (VGs) are often installed on the flaps of high-lift systems of aircraft as retrofit devices for increasing the lift by suppressing flow separation. To reduce the number of VGs, increasing their heights is a viable solution for generating strong vortices. However, the maximum size of the VGs cannot be determined based on the available literature. We investigated the effect of size of a vane-type rectangular VG on the lift force of a half-span high-lift swept-back wing model. The experiments were performed in a low-speed wind tunnel at Reynolds number 1.86 × $ 10^{6} $. In this study, three different heights (Hv) of the VGs with co-rotating vortex configurations were tested, all of which were larger than the boundary layer thickness δ at the VG’s installation position of the flap. We observed that moderately sized VGs (Hv/δ = 4.8) maximized the increase in the lift coefficient, while excessively large VGs (Hv/δ = 9.6) reduced this increase. To examine this further, we measured the flow fields over the flap for VGs with both Hv/δ = 4.8 and 9.6 via stereoscopic particle image velocimetry. Results showed that VGs with Hv/δ = 9.6 generated a larger flow separation area as compared to that with Hv/δ = 4.8. For Hv/δ = 9.6, almost half of the vortex core interacted with the main wing wake; this implies that vortices generated by VGs with Hv/δ = 9.6 produce low-momentum fluid entrainment in the wake toward the boundary layer on the flap, thus diminishing the effect of the VGs. Graphic abstract Koike, S. aut Ito, Y. aut Murayama, M. aut Nakakita, K. aut Yamamoto, K. aut Kusunose, K. aut Enthalten in Experiments in fluids Springer Berlin Heidelberg, 1983 62(2021), 8 vom: 12. Juli (DE-627)130443794 (DE-600)710083-8 (DE-576)015977404 0723-4864 nnns volume:62 year:2021 number:8 day:12 month:07 https://doi.org/10.1007/s00348-021-03198-4 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-PHY GBV_ILN_2018 GBV_ILN_4277 AR 62 2021 8 12 07 |
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10.1007/s00348-021-03198-4 doi (DE-627)OLC2126583511 (DE-He213)s00348-021-03198-4-p DE-627 ger DE-627 rakwb eng 620 530 VZ 530 VZ Ichikawa, Y. verfasserin aut Size effects of vane-type rectangular vortex generators installed on high-lift swept-back wing flap on lift force and flow fields 2021 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © The Author(s), under exclusive licence to Springer-Verlag GmbH Germany, part of Springer Nature 2021 Abstract Vane-type vortex generators (VGs) are often installed on the flaps of high-lift systems of aircraft as retrofit devices for increasing the lift by suppressing flow separation. To reduce the number of VGs, increasing their heights is a viable solution for generating strong vortices. However, the maximum size of the VGs cannot be determined based on the available literature. We investigated the effect of size of a vane-type rectangular VG on the lift force of a half-span high-lift swept-back wing model. The experiments were performed in a low-speed wind tunnel at Reynolds number 1.86 × $ 10^{6} $. In this study, three different heights (Hv) of the VGs with co-rotating vortex configurations were tested, all of which were larger than the boundary layer thickness δ at the VG’s installation position of the flap. We observed that moderately sized VGs (Hv/δ = 4.8) maximized the increase in the lift coefficient, while excessively large VGs (Hv/δ = 9.6) reduced this increase. To examine this further, we measured the flow fields over the flap for VGs with both Hv/δ = 4.8 and 9.6 via stereoscopic particle image velocimetry. Results showed that VGs with Hv/δ = 9.6 generated a larger flow separation area as compared to that with Hv/δ = 4.8. For Hv/δ = 9.6, almost half of the vortex core interacted with the main wing wake; this implies that vortices generated by VGs with Hv/δ = 9.6 produce low-momentum fluid entrainment in the wake toward the boundary layer on the flap, thus diminishing the effect of the VGs. Graphic abstract Koike, S. aut Ito, Y. aut Murayama, M. aut Nakakita, K. aut Yamamoto, K. aut Kusunose, K. aut Enthalten in Experiments in fluids Springer Berlin Heidelberg, 1983 62(2021), 8 vom: 12. Juli (DE-627)130443794 (DE-600)710083-8 (DE-576)015977404 0723-4864 nnns volume:62 year:2021 number:8 day:12 month:07 https://doi.org/10.1007/s00348-021-03198-4 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-PHY GBV_ILN_2018 GBV_ILN_4277 AR 62 2021 8 12 07 |
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10.1007/s00348-021-03198-4 doi (DE-627)OLC2126583511 (DE-He213)s00348-021-03198-4-p DE-627 ger DE-627 rakwb eng 620 530 VZ 530 VZ Ichikawa, Y. verfasserin aut Size effects of vane-type rectangular vortex generators installed on high-lift swept-back wing flap on lift force and flow fields 2021 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © The Author(s), under exclusive licence to Springer-Verlag GmbH Germany, part of Springer Nature 2021 Abstract Vane-type vortex generators (VGs) are often installed on the flaps of high-lift systems of aircraft as retrofit devices for increasing the lift by suppressing flow separation. To reduce the number of VGs, increasing their heights is a viable solution for generating strong vortices. However, the maximum size of the VGs cannot be determined based on the available literature. We investigated the effect of size of a vane-type rectangular VG on the lift force of a half-span high-lift swept-back wing model. The experiments were performed in a low-speed wind tunnel at Reynolds number 1.86 × $ 10^{6} $. In this study, three different heights (Hv) of the VGs with co-rotating vortex configurations were tested, all of which were larger than the boundary layer thickness δ at the VG’s installation position of the flap. We observed that moderately sized VGs (Hv/δ = 4.8) maximized the increase in the lift coefficient, while excessively large VGs (Hv/δ = 9.6) reduced this increase. To examine this further, we measured the flow fields over the flap for VGs with both Hv/δ = 4.8 and 9.6 via stereoscopic particle image velocimetry. Results showed that VGs with Hv/δ = 9.6 generated a larger flow separation area as compared to that with Hv/δ = 4.8. For Hv/δ = 9.6, almost half of the vortex core interacted with the main wing wake; this implies that vortices generated by VGs with Hv/δ = 9.6 produce low-momentum fluid entrainment in the wake toward the boundary layer on the flap, thus diminishing the effect of the VGs. Graphic abstract Koike, S. aut Ito, Y. aut Murayama, M. aut Nakakita, K. aut Yamamoto, K. aut Kusunose, K. aut Enthalten in Experiments in fluids Springer Berlin Heidelberg, 1983 62(2021), 8 vom: 12. Juli (DE-627)130443794 (DE-600)710083-8 (DE-576)015977404 0723-4864 nnns volume:62 year:2021 number:8 day:12 month:07 https://doi.org/10.1007/s00348-021-03198-4 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-PHY GBV_ILN_2018 GBV_ILN_4277 AR 62 2021 8 12 07 |
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Size effects of vane-type rectangular vortex generators installed on high-lift swept-back wing flap on lift force and flow fields |
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Size effects of vane-type rectangular vortex generators installed on high-lift swept-back wing flap on lift force and flow fields |
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Ichikawa, Y. |
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Experiments in fluids |
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Ichikawa, Y. Koike, S. Ito, Y. Murayama, M. Nakakita, K. Yamamoto, K. Kusunose, K. |
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Ichikawa, Y. |
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10.1007/s00348-021-03198-4 |
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size effects of vane-type rectangular vortex generators installed on high-lift swept-back wing flap on lift force and flow fields |
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Size effects of vane-type rectangular vortex generators installed on high-lift swept-back wing flap on lift force and flow fields |
| abstract |
Abstract Vane-type vortex generators (VGs) are often installed on the flaps of high-lift systems of aircraft as retrofit devices for increasing the lift by suppressing flow separation. To reduce the number of VGs, increasing their heights is a viable solution for generating strong vortices. However, the maximum size of the VGs cannot be determined based on the available literature. We investigated the effect of size of a vane-type rectangular VG on the lift force of a half-span high-lift swept-back wing model. The experiments were performed in a low-speed wind tunnel at Reynolds number 1.86 × $ 10^{6} $. In this study, three different heights (Hv) of the VGs with co-rotating vortex configurations were tested, all of which were larger than the boundary layer thickness δ at the VG’s installation position of the flap. We observed that moderately sized VGs (Hv/δ = 4.8) maximized the increase in the lift coefficient, while excessively large VGs (Hv/δ = 9.6) reduced this increase. To examine this further, we measured the flow fields over the flap for VGs with both Hv/δ = 4.8 and 9.6 via stereoscopic particle image velocimetry. Results showed that VGs with Hv/δ = 9.6 generated a larger flow separation area as compared to that with Hv/δ = 4.8. For Hv/δ = 9.6, almost half of the vortex core interacted with the main wing wake; this implies that vortices generated by VGs with Hv/δ = 9.6 produce low-momentum fluid entrainment in the wake toward the boundary layer on the flap, thus diminishing the effect of the VGs. Graphic abstract © The Author(s), under exclusive licence to Springer-Verlag GmbH Germany, part of Springer Nature 2021 |
| abstractGer |
Abstract Vane-type vortex generators (VGs) are often installed on the flaps of high-lift systems of aircraft as retrofit devices for increasing the lift by suppressing flow separation. To reduce the number of VGs, increasing their heights is a viable solution for generating strong vortices. However, the maximum size of the VGs cannot be determined based on the available literature. We investigated the effect of size of a vane-type rectangular VG on the lift force of a half-span high-lift swept-back wing model. The experiments were performed in a low-speed wind tunnel at Reynolds number 1.86 × $ 10^{6} $. In this study, three different heights (Hv) of the VGs with co-rotating vortex configurations were tested, all of which were larger than the boundary layer thickness δ at the VG’s installation position of the flap. We observed that moderately sized VGs (Hv/δ = 4.8) maximized the increase in the lift coefficient, while excessively large VGs (Hv/δ = 9.6) reduced this increase. To examine this further, we measured the flow fields over the flap for VGs with both Hv/δ = 4.8 and 9.6 via stereoscopic particle image velocimetry. Results showed that VGs with Hv/δ = 9.6 generated a larger flow separation area as compared to that with Hv/δ = 4.8. For Hv/δ = 9.6, almost half of the vortex core interacted with the main wing wake; this implies that vortices generated by VGs with Hv/δ = 9.6 produce low-momentum fluid entrainment in the wake toward the boundary layer on the flap, thus diminishing the effect of the VGs. Graphic abstract © The Author(s), under exclusive licence to Springer-Verlag GmbH Germany, part of Springer Nature 2021 |
| abstract_unstemmed |
Abstract Vane-type vortex generators (VGs) are often installed on the flaps of high-lift systems of aircraft as retrofit devices for increasing the lift by suppressing flow separation. To reduce the number of VGs, increasing their heights is a viable solution for generating strong vortices. However, the maximum size of the VGs cannot be determined based on the available literature. We investigated the effect of size of a vane-type rectangular VG on the lift force of a half-span high-lift swept-back wing model. The experiments were performed in a low-speed wind tunnel at Reynolds number 1.86 × $ 10^{6} $. In this study, three different heights (Hv) of the VGs with co-rotating vortex configurations were tested, all of which were larger than the boundary layer thickness δ at the VG’s installation position of the flap. We observed that moderately sized VGs (Hv/δ = 4.8) maximized the increase in the lift coefficient, while excessively large VGs (Hv/δ = 9.6) reduced this increase. To examine this further, we measured the flow fields over the flap for VGs with both Hv/δ = 4.8 and 9.6 via stereoscopic particle image velocimetry. Results showed that VGs with Hv/δ = 9.6 generated a larger flow separation area as compared to that with Hv/δ = 4.8. For Hv/δ = 9.6, almost half of the vortex core interacted with the main wing wake; this implies that vortices generated by VGs with Hv/δ = 9.6 produce low-momentum fluid entrainment in the wake toward the boundary layer on the flap, thus diminishing the effect of the VGs. Graphic abstract © The Author(s), under exclusive licence to Springer-Verlag GmbH Germany, part of Springer Nature 2021 |
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Size effects of vane-type rectangular vortex generators installed on high-lift swept-back wing flap on lift force and flow fields |
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Koike, S. Ito, Y. Murayama, M. Nakakita, K. Yamamoto, K. Kusunose, K. |
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