Numerical and experimental investigation of airfoil derived from peregrine FALCON

In this work, the Peregrine falcon's airfoil is derived and is analysed numerically and experimentally in a non-flapping, non-morphing case. The airfoil is analysed numerically using a Steady State RANS k-ω SST model at different Reynolds numbers with ANSYS Fluent solver and is compared with NACA 23015 and NACA 64–210. The numerical method of approach is validated at a high Reynolds number of 1x106 experimentally. The results dictate that FALCON airfoil has a cl, max that is 54 % and 118 % higher than NACA 23015 and NACA 64–210 respectively. Stalling at 12oangle of attack, the airfoil generates an (LD) of 84, and produces positive lift coefficients till -5o angle of attack. The cl of FALCON is higher than the NACA 64–210 and 23015 at all angles of attack. The variation of (LD) with AoA is smooth and of a parabolic nature than an abrupt one.