Abstract
In this current research work, a NACA 6321 flat bottom aerofoil has been altered to study its aerodynamic performance. A co-flow jet (CFJ) method was used with an injection slot located at 20% of chord length and the suction slot situated at 80% of chord length. Simulations have been carried out on the aerofoil models with various angles of attack (AOA) at a Mach number 0.05 to compute the variation in coefficient of lift (CL) and coefficient of drag (Cd) using a k-omega SST model. From the study, it was observed that CL and stalling AOA of an aircraft are increased by 27% and 33% respectively, with an introduction of the additional mass flow rate of 0.01 kg/sec in comparison with baseline aerofoil. It could be concluded that CFJ method enhanced the aerodynamic performance of fixed-wing aircraft due to boundary layer control over an aerofoil which reduces the overall aircraft weight and maintenance cost.
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