Kinetic Energy Projectile popularly known as Fin Stabilized Armoured Piercing Discarded Sabot (FSAPDS), damages the enemy tanks by penetrating the thick armour of the tank. FSAPDS needs to be designed to offer lower drag to keep higher momentum and required stability margin to attain an undisturbed flight to cause damage to the armour plates of main battle tanks. Therefore, aerodynamic configuration design plays a crucial role to achieve minimum drop in flight projectile velocity and to provide necessary stability margin with the help of fin stabilizers. The present study focuses on the parametric aerodynamic configuration design studies which are carried out to achieve drop in velocity less than 80 m/s during the trajectory of projectile. The aerodynamic configuration design mainly consists of parametric approach applied with the help of in-house semi-empirical code and CFD simulations. Various geometrical parameters of the nose, body and fins are varied to achieve required objective of stability margin (of the order of 3–4 Calibres) along with the criteria of minimum drop in velocity. In the present study, Computational Fluid Dynamics (CFD) simulations are carried out using MIME and CFD++ software to obtain high fidelity results. The effect of variation in geometrical parameters with help of Semi-Empirical methods and CFD are presented in the present work. The studies presented in this paper will be very beneficial and quick reference for the aerodynamic design of the kinetic energy projectile (FSAPDS).