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- W2999065362 abstract "This study includes a numerical simulation to investigate the aerodynamic behavior of the air flow around the surface of the NACA0012 airfoil, with and without a triangular rib. The triangular rib was used on the upper surface of the airfoil with size of 2% of the total chord length and variously located at 50, 70 and 90 percent of the chord length from the leading edge, separately as a passive control technique. Workbench-Fluent 17.2 version software was used to simulate the flow at 7 m/s freestream velocity (Re = 78,000), various attack angles (0˚ to 22˚) and chord length of 168 mm. The results indicated the presence of the triangular rib on the airfoil's upper surface, at low angles of attack (less than 12˚), was a negative for the lift and drag results, at the angle of 12˚ it was a positive only for the location of 90%, while at the higher angles it was a positive for all locations and for all results where the lift increased and drag decreased. Therefore, the NACA0012 airfoil's performance (lift to drag ratio) was significantly enhanced but, at 22˚, it had a very small effect for all results. It was concluded that the rib's presence at 50% location delayed the stall angle by two degrees (from 14˚ to 16˚)." @default.
- W2999065362 created "2020-01-23" @default.
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- W2999065362 date "2020-01-17" @default.
- W2999065362 modified "2023-10-16" @default.
- W2999065362 title "Numerical Study of the Boundary Layer Separation Control on the NACA 0012 Airfoil using Triangular Rib" @default.
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- W2999065362 doi "https://doi.org/10.1088/1757-899x/671/1/012144" @default.
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