Investigation of an Aerofoil Using Improved Blowing Suction System

The aim of this paper is to experimentally verify the aerodynamic performance enhancement of the novel Improved Blowing Suction System (IBSS) in an aerofoil by regulating the top surface’s boundary layer. NACA6321 baseline and IBSS aerofoil with injection and suction are fabricated to carry out tests at a Mach number of 0.10 with a constant jet momentum coefficient of 0.037. It is established that the IBSS approach significantly improves the aerodynamics properties of the aerofoil. According to the experimental data, the stall angle is 40% better, the lift coefficient is 54% higher, and the drag coefficient is 33% lower than it was for the baseline aerofoil. This analysis also demonstrates that in order to enhance aerodynamic performance and to lower power consumption and related losses, the injection slot must be located near to the peak thickness of an aerofoil. Additionally, the IBSS approach is proven to work better across all flight phases with a constant injection and suction cross section.