Abstract
In this paper NACA 2421 Aerofoil is analyzed at several angles of attack ranging from -200 to 200 and with the Reynolds number at 1.8 × 105 and the velocity are 20 m/s. The co-efficient of lift and drag are compared with the standard values in the literature. Variation of pressure co-efficient is plotted in the form of contour. The aerofoil is designed in ANSYS and it is imported to Computational Fluid Dynamics and the variations of CL and CD with respect to various angles of attack is analyzed.
Highlights
The NACA 2421 Aerofoil is designed for subsonic aircraft wings because of the better performance
In this work the flow separation over NACA 2421 unsymmetrical airfoil is observed and steps are taken to increase the lift to drag ratio [2]
The lift to drag ratio, critical angles of attack and stall regions are analyzed over the NACA 2421 Aerofoil with the various angles of attack [1]
Summary
The NACA 2421 Aerofoil is designed for subsonic aircraft wings because of the better performance. Significance of improving a UAV performance can be done at very low Reynolds number 1.8 × 105. Flow separation occurs normally due to very low inertia and very high viscosity [1]. In general NACA 2421 Aerofoil generates more lift in subsonic speed
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