Aerodynamic Performance Assessment of Distributed Electric Propulsion after the Wing Trailing Edge
Distributed electric propulsion (DEP) with four propellers distributed along the rear edge of the wing (pusher DEP configuration) promote aerodynamic interactions to a higher level. To study the aerodynamic performance of DEP with the rear wing through simulations and experiments, the multi-referenc...
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| Format: | Article |
| Language: | English |
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MDPI AG
2023-12-01
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| Series: | Applied Sciences |
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| Online Access: | https://www.mdpi.com/2076-3417/14/1/280 |
| _version_ | 1797359053215629312 |
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| author | Yao Lei Xiangzheng Zhao |
| author_facet | Yao Lei Xiangzheng Zhao |
| author_sort | Yao Lei |
| collection | DOAJ |
| description | Distributed electric propulsion (DEP) with four propellers distributed along the rear edge of the wing (pusher DEP configuration) promote aerodynamic interactions to a higher level. To study the aerodynamic performance of DEP with the rear wing through simulations and experiments, the multi-reference frame (MRF) with sliding grid is combined with wind tunnel tests. The obtained results demonstrate that the lift and drag of DEP increase with the angle of attack (AoA) and are related to the relative position of the propellers and wing. The propeller has no significant effect on the lift of the wing, and the lift and the AoA remain linear when the AoA is less than 16°. By contrast, the lift coefficient is much higher than the baseline (isolated wing), and the lift is greatly improved with the increasing drag when the AoA is greater than 16°. This is because the flow around the wing of the pusher configuration remains attached due to the suction of the inflow of the propeller on the trailing edge vortex. In addition, the acceleration effect on the free flow improves the kinetic energy of the airflow, which effectively delays the separation of the airflow in the slipstream region. |
| first_indexed | 2024-03-08T15:11:25Z |
| format | Article |
| id | doaj.art-1f7531528bfd478781aa33d4444aba0c |
| institution | Directory Open Access Journal |
| issn | 2076-3417 |
| language | English |
| last_indexed | 2024-03-08T15:11:25Z |
| publishDate | 2023-12-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Applied Sciences |
| spelling | doaj.art-1f7531528bfd478781aa33d4444aba0c2024-01-10T14:51:35ZengMDPI AGApplied Sciences2076-34172023-12-0114128010.3390/app14010280Aerodynamic Performance Assessment of Distributed Electric Propulsion after the Wing Trailing EdgeYao Lei0Xiangzheng Zhao1School of Mechanical Engineering and Automation, Fuzhou University, Fuzhou 350116, ChinaSchool of Mechanical Engineering and Automation, Fuzhou University, Fuzhou 350116, ChinaDistributed electric propulsion (DEP) with four propellers distributed along the rear edge of the wing (pusher DEP configuration) promote aerodynamic interactions to a higher level. To study the aerodynamic performance of DEP with the rear wing through simulations and experiments, the multi-reference frame (MRF) with sliding grid is combined with wind tunnel tests. The obtained results demonstrate that the lift and drag of DEP increase with the angle of attack (AoA) and are related to the relative position of the propellers and wing. The propeller has no significant effect on the lift of the wing, and the lift and the AoA remain linear when the AoA is less than 16°. By contrast, the lift coefficient is much higher than the baseline (isolated wing), and the lift is greatly improved with the increasing drag when the AoA is greater than 16°. This is because the flow around the wing of the pusher configuration remains attached due to the suction of the inflow of the propeller on the trailing edge vortex. In addition, the acceleration effect on the free flow improves the kinetic energy of the airflow, which effectively delays the separation of the airflow in the slipstream region.https://www.mdpi.com/2076-3417/14/1/280distributed propulsionaerodynamic interactionswind tunnel testsnumerical solution |
| spellingShingle | Yao Lei Xiangzheng Zhao Aerodynamic Performance Assessment of Distributed Electric Propulsion after the Wing Trailing Edge Applied Sciences distributed propulsion aerodynamic interactions wind tunnel tests numerical solution |
| title | Aerodynamic Performance Assessment of Distributed Electric Propulsion after the Wing Trailing Edge |
| title_full | Aerodynamic Performance Assessment of Distributed Electric Propulsion after the Wing Trailing Edge |
| title_fullStr | Aerodynamic Performance Assessment of Distributed Electric Propulsion after the Wing Trailing Edge |
| title_full_unstemmed | Aerodynamic Performance Assessment of Distributed Electric Propulsion after the Wing Trailing Edge |
| title_short | Aerodynamic Performance Assessment of Distributed Electric Propulsion after the Wing Trailing Edge |
| title_sort | aerodynamic performance assessment of distributed electric propulsion after the wing trailing edge |
| topic | distributed propulsion aerodynamic interactions wind tunnel tests numerical solution |
| url | https://www.mdpi.com/2076-3417/14/1/280 |
| work_keys_str_mv | AT yaolei aerodynamicperformanceassessmentofdistributedelectricpropulsionafterthewingtrailingedge AT xiangzhengzhao aerodynamicperformanceassessmentofdistributedelectricpropulsionafterthewingtrailingedge |