Numerical simulation of aerofoil with flow injection at the upper surface
Separation of the boundary layer over an airfoil causes a significant increase in the adverse pressure gradients and the losses of energy resulting in the reduction of the lift force and the increment of drag force. Therefore, delaying and eliminating flow separation is necessary to improve its aero...
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| Format: | Article |
| Language: | English |
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Penerbit Akademia Baru
2020
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| Online Access: | http://eprints.uthm.edu.my/6308/ http://eprints.uthm.edu.my/6308/1/AJ%202020%20%28268%29.pdf |
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| author | Chua, Bing Liang Mohammed, Akmal Nizam Sapit, Azwan Razali, Mohd Azahari Hushim, Mohd Faisal Khalid, Amir Mohd Yusof, Nurul Farhana |
| author_facet | Chua, Bing Liang Mohammed, Akmal Nizam Sapit, Azwan Razali, Mohd Azahari Hushim, Mohd Faisal Khalid, Amir Mohd Yusof, Nurul Farhana |
| author_sort | Chua, Bing Liang |
| building | UTHM Institutional Repository |
| collection | Online Access |
| description | Separation of the boundary layer over an airfoil causes a significant increase in the adverse pressure gradients and the losses of energy resulting in the reduction of the lift force and the increment of drag force. Therefore, delaying and eliminating flow separation is necessary to improve its aerodynamic characteristics. In this study, an injection of flow was introduced at the upper surface/suction side of the aerofoil to control the boundary layer separation effectively. Flow around the NACA0012 airfoil was examined, with the position of flow injection jet at 90° relative to the tangential surface of the airfoil at 20%, 50% and 80% of its chord length. The flow injection velocity was varied from 0%, 10%, 30% and 50% of the free stream velocity, which corresponds to 0, 2.5 x 10-4, 2.25 x 10-3 and 6.25 x 10-3 of the momentum coefficient. The results showed that the most suitable condition was at 10% of the blowing amplitude (2.5 x 10-4 of the momentum coefficient) of flow injection at the trailing edge, which was around 80% of the chord length at the upper surface/suction side. This configuration can successfully increase the lift force and decrease the drag force of the aerofoil at the angle equal to or larger than a stall angle of 16° compared to the baseline aerofoil. |
| first_indexed | 2025-11-15T20:15:37Z |
| format | Article |
| id | uthm-6308 |
| institution | Universiti Tun Hussein Onn Malaysia |
| institution_category | Local University |
| language | English |
| last_indexed | 2025-11-15T20:15:37Z |
| publishDate | 2020 |
| publisher | Penerbit Akademia Baru |
| recordtype | eprints |
| repository_type | Digital Repository |
| spelling | uthm-63082022-01-30T01:56:22Z http://eprints.uthm.edu.my/6308/ Numerical simulation of aerofoil with flow injection at the upper surface Chua, Bing Liang Mohammed, Akmal Nizam Sapit, Azwan Razali, Mohd Azahari Hushim, Mohd Faisal Khalid, Amir Mohd Yusof, Nurul Farhana T Technology (General) TJ Mechanical engineering and machinery Separation of the boundary layer over an airfoil causes a significant increase in the adverse pressure gradients and the losses of energy resulting in the reduction of the lift force and the increment of drag force. Therefore, delaying and eliminating flow separation is necessary to improve its aerodynamic characteristics. In this study, an injection of flow was introduced at the upper surface/suction side of the aerofoil to control the boundary layer separation effectively. Flow around the NACA0012 airfoil was examined, with the position of flow injection jet at 90° relative to the tangential surface of the airfoil at 20%, 50% and 80% of its chord length. The flow injection velocity was varied from 0%, 10%, 30% and 50% of the free stream velocity, which corresponds to 0, 2.5 x 10-4, 2.25 x 10-3 and 6.25 x 10-3 of the momentum coefficient. The results showed that the most suitable condition was at 10% of the blowing amplitude (2.5 x 10-4 of the momentum coefficient) of flow injection at the trailing edge, which was around 80% of the chord length at the upper surface/suction side. This configuration can successfully increase the lift force and decrease the drag force of the aerofoil at the angle equal to or larger than a stall angle of 16° compared to the baseline aerofoil. Penerbit Akademia Baru 2020 Article PeerReviewed text en http://eprints.uthm.edu.my/6308/1/AJ%202020%20%28268%29.pdf Chua, Bing Liang and Mohammed, Akmal Nizam and Sapit, Azwan and Razali, Mohd Azahari and Hushim, Mohd Faisal and Khalid, Amir and Mohd Yusof, Nurul Farhana (2020) Numerical simulation of aerofoil with flow injection at the upper surface. CFD Letters, 12 (1). pp. 98-110. ISSN 2180-1363 |
| spellingShingle | T Technology (General) TJ Mechanical engineering and machinery Chua, Bing Liang Mohammed, Akmal Nizam Sapit, Azwan Razali, Mohd Azahari Hushim, Mohd Faisal Khalid, Amir Mohd Yusof, Nurul Farhana Numerical simulation of aerofoil with flow injection at the upper surface |
| title | Numerical simulation of aerofoil with flow injection at the upper surface |
| title_full | Numerical simulation of aerofoil with flow injection at the upper surface |
| title_fullStr | Numerical simulation of aerofoil with flow injection at the upper surface |
| title_full_unstemmed | Numerical simulation of aerofoil with flow injection at the upper surface |
| title_short | Numerical simulation of aerofoil with flow injection at the upper surface |
| title_sort | numerical simulation of aerofoil with flow injection at the upper surface |
| topic | T Technology (General) TJ Mechanical engineering and machinery |
| url | http://eprints.uthm.edu.my/6308/ http://eprints.uthm.edu.my/6308/1/AJ%202020%20%28268%29.pdf |