![]() A decrease in accreted ice mass and thickness is observed with the increase of airfoil geometric size. The parametric analysis of the ice accretion at different operating and geometric conditions show an increase in the ice growth with the increase in air velocity and droplet size, whereas a change in the atmospheric temperature significantly affects the accreted ice shapes. The analysis shows a decrease in the aerodynamic characteristics of the iced airfoils as compared to the clean airfoil. This noise reduction effect becomes greater with. Increases in both leading edge radius and thickness are found to reduce the predicted noise. Aerodynamic characteristics of both airfoils for clean and iced conditions were analyzed at different angles of attack ranging from −16° to +16°. The effects of airfoil thickness and leading edge radius on noise are investigated systematically and independently for the first time, at higher frequencies than previously used in computational methods. Wings of insects such as dragonfly have high aspect ratios and typically have chord lengths and thickness of only few mm. In the present study the maximum thickness of 12mm was chosen with a chord length of 120mm. Streamline ice shapes are observed in the case of symmetric airfoil in comparison to the ones found for the asymmetric airfoil. Since NACA 0010 is symmetric airfoil the camber for such airfoils is zero while thickness to chord ratio is 10. ![]() ![]() The results show that the airfoil geometric shape and size has an effect on the rate and shape of ice accretion. Transcribed image text: A symmetric airfoil is at an angle of attack of 3 in a flow with freestream properties Vo 25 m/s and pro 1193 kg/m3 The chord of the airfoil is c 10 m The airfoil is modeled using a vortex sheet with strength given by 7(0) B(x-ack +c) m/s where x is the position along the chord and a and Bare constants. The present study numerically, investigates the aerodynamic characteristics of low speed flow past symmetric NACA airfoils, for various t/c values of 0.10, 0.15, 0.18, 0.21 and 0.24 at chordwise Reynolds numbers of 2 × 10 5 and 4 × 10 5, where t is the airfoil thickness and c is the airfoil chord. A parametric numerical study of ice accretion along symmetric (NACA-0012) and asymmetric (NACA-23012) airfoils has been carried out at different operating and geometric conditions with the aim to better understand the ice accretion along wind turbine blades.
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