Affiliation:
1. GITAM University (Deemed), India
2. Thales Pvt. Ltd., India
Abstract
This research aims to examine the flow field over a NACA 651-412 aerofoil at a supersonic Mach number (M = 2) in the presence of a sharp spike and a Hemi spherical head spike. Using a spike integrated with an aerofoil alters the flow characteristics of the aerofoil, resulting in changes in aerodynamic lift and drag. Flow visualisation graphs and coefficients of aerodynamic drag and lift are measured. In this work, two spike designs were employed: sharp edges and hemispherical edges. The flow over an aerofoil with and without a spike is also compared in order to comprehend the performance of the NACA 6 series aerofoil with different geometry alteration. For computational simulation, ICEM CFD is used as a meshing tool and ANSYS fluent as an adjoint solver to analyse the external flow over the body. Furthermore, the drag increases significantly when the flight angle of attack increases. Employing certain installation angles effectively improves the drag reduction around the angle of attack and improve the lift-to-drag ratio.
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