The tubercle effect is a recently discovered phenomenon where the sinusoidal pattem ‘bumps’ on the leading edge of an airfoil can improve the aerodynamic performance. This effect was inspired by looking at the humpback whale pectoral flippers that give an exceptional acrobatic manoeuvrability in the water such as somersaults, also allowing for easier capture of prey. The objective of this research is to study the effect of implementing the tubercles concept on the car spoiler in order to see whether it bring advantage or disadvantage in the aerodynamic performance of a car. The design and simulation process are done by using Solidworks. The design of airfoil spoiler based on Selig S2091 (low Reynolds number airfoil) with sinusoidal pattern leading edge were computationally used. The Airfoil spoiler with 270 mm of the chord length (C), 1200 mm wingspan (L) and angles of attack of -5°, 0°, 5°, 10°, 15°, 20°, 25°, 30° were improvised with tubercles at 40 mm amplitude of bumps (h) and the distance of the wavelength between peaks (λ) of 1200 mm, 240 mm and 133.33 mm. The simulation was tested at 40 m/s. The investigation shown that the tubercles can improve the aerodynamic performance of car rear spoiler where the tubercles are able to increase the lift coefficient but has a significant decrease in drag only at 20° and above angle of attack.
Eagle is one of the most manoeuvrable and aerodynamically efficient bird capable of soaring for a mile, and it has high gliding ratio that can reach high velocities. Unmanned Aerial Vehicles () used in military and civilian applications are required to loiter at significant altitude without being targeted by observers. However, the induced drag is usually held mainly at the wingtip, which affects the performance of the in steady state condition due to wingtip vortex. Therefore, the objectives of this paper are to study the effect of multi-winglet on different configurations in the performance of lift and drag coefficients and to analyse the flow pattern of multi-winglet with difference configurations. The wing airfoil used was with chord length of and wingspan of . The multi-winglet device was simulated using software with three, five and seven multi-winglet configurations at angles of attack between -5° to 20° (with increment of 5°) and at flying speed of . This study found that seven multi-winglets demonstrated better results in lift and drag coefficients compared to other models at low angles of attack. In conclusion, multi-winglets can improve the aerodynamic performance of airfoil in reducing the induced drag and increasing the lift coefficient, which is suitable to be implemented at low angles of attack due to the bluffing body of winglet at high angles of attack.
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