CFD-Based Leading Edge Analysis of Aircraft Wing Aerofoil

The selection and design of aerofoils is the most important step in the aircraft design process. An aerofoil is the crosssectional
geometry of a wing that generates aerodynamic forces. When several aerofoils are piled together, they form a
wing. The wing generates lift force, which counteracts the downward weight force. A complete examination of the
shock, boundary layer, and other flow parameters must be undertaken before selecting any aerofoil for supersonic
aircraft. Aerodynamic analysis is used to determine the vehicle's lift and drag coefficients, as well as estimate highand
low-pressure zones and separation points that affect vehicle performance. This analysis was done with CFDFluent,
which is a fluid mechanics programme. For analysing and processing problems involving fluid flow, data
structure and numerical analysis are used. The results of the aerodynamic analysis provide information on the many
parameters and properties of the NACA 64-008A aerofoil. The analysis of a NACA 64 series supersonic aerofoil is the
subject of this paper. The coefficients of lift and drag for three distinct leading edge radius at Mach 1.5 with a variable
angle of attack are investigated. Pressure, velocity, and velocity stream line have been examined over the top and
bottom surfaces of the NACA 64-008A aerofoil using Computational Fluid Dynamics.