Numerical simulation of aerofoil with flow injection at the upper surface

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

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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.

Item Type: Article
Uncontrolled Keywords: CFD; Flow Injection; Airfoil; NACA0012
Subjects: T Technology > T Technology (General)
T Technology > TJ Mechanical engineering and machinery
Divisions: Faculty of Mechanical and Manufacturing Engineering > Department of Mechanical Engineering
Depositing User: Miss Afiqah Faiqah Mohd Hafiz
Date Deposited: 30 Jan 2022 01:56
Last Modified: 30 Jan 2022 01:56

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