Development and Assessment of an Inviscid Source Vortex Panel Method for Low-Reynolds Number Airfoil Cascades

In this study, a source vortex panel method (SVPM) is developed for 2-D airfoil flows in cascade based on the potential flow theory. The accuracy and limitations of the proposed methodology are assessed through comprehensive validation against available experimental data. Interference factors due to the cascade effect are derived using this inviscid approach, and employed to adjust the force information obtained from isolated airfoils. The SVPM demonstrates good predictions for the lift and pressure coefficients of 2-D cascades with Reynolds numbers exceeding 1.84×10⁵, turbulence levels over around 2.5%, and low-to-moderate angles of attack. The interference factors also effectively modify lift coefficients from isolated airfoils for low angle of attack cases. The results provide insights into applying a potential flow method to low-Reynolds number airfoil cascades, facilitating the design and optimization of small-scaled axial fans.