Experimental and Numerical Analysis on Co-Flow Jet Airfoil
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Abstract
This project undertakes a comprehensive investigation into the aerodynamic behaviours of NACA 0018 baseline and co-flow jet (CFJ) airfoils, employing both wind tunnel tests and numerical methodologies using ANSYS Fluent. Through detailed analysis of lift coefficient (CL), stalling Angle of Attack (AoA) and drag coefficient (CD), the study aims to discern distinct characteristics between the two airfoil configurations. CFJ airfoil emerges as notably superior, showcasing enhanced lift augmentation and stall resistance, with CL values approximately 17% higher in numerical simulations and 50% higher in test compared to NACA 0018 airfoil. The project emphasizes the significance of validation procedures, especially in light of discrepancies between experimental and numerical findings. Employing an advanced pressure-based algorithm alongside the Spalart-Allmaras turbulence model for numerical simulations, the study delves into transient 2D incompressible flow phenomena, employing the Reynolds-Averaged Navier-Stokes (RANS) equations. Through spatial discretization utilizing the 2nd order upwind approach and employing a convergence criterion of 1e-8 for the iterative process, computational efficiency is maximized.
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