Wing Simulation Using Naca 0018 and 0024 and Aluminum Alloy 7075 T6-SN and 7050-T7451 Materials for Lift and Drag

Pane, Medyawanti (2024) Wing Simulation Using Naca 0018 and 0024 and Aluminum Alloy 7075 T6-SN and 7050-T7451 Materials for Lift and Drag. JOURNAL OF MECHANICAL ENGINEERING, MANUFACTURES, MATERIALS AND ENERGY, 8 (2). pp. 191-200. ISSN 2549-6239

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Abstract

The analysis of an airplane wing's airfoil shape plays a critical role in determining aerodynamic performance, specifically impacting lift and drag forces. This study investigates two aluminum alloys, Aluminum Alloy 7075-T6 SN and Aluminum Alloy 7050-T7451, to evaluate their effectiveness in enhancing lift and drag on NACA 0018 and NACA 0024 airfoil profiles. Using the ANSYS Fluent software, simulations are conducted at an airflow speed of 200 m/s to analyze pressure contours and velocity contours associated with each material. The results indicate that Aluminum Alloy 7075-T6 SN yields the highest lift and drag coefficients for both airfoil profiles. For NACA 0018, the lift coefficient reaches 6.83 N, while the drag coefficient is 6.89 N. Similarly, for NACA 0024, the lift coefficient is observed at 3.23 N, and the drag coefficient at 4.64 N when using Aluminum Alloy 7075-T6 SN. These findings suggest that Aluminum Alloy 7075-T6 SN offers superior performance in optimizing the aerodynamic forces of lift and drag for these airfoil designs. The study’s insights could inform material selection for airfoil design, enhancing efficiency in various aerodynamic applications. Keywords: NACA Airfoil; Aluminum Alloy; ANSYS Fluent

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