Optimized Hermite Interpolation for Geometrically and Aerodynamically Consistent Airfoil Reconstruction in Computational Fluid Dynamics

Airfoil profiles form the foundation of flight performance by determining the balance between lift and drag forces. Computational Fluid Dynamics (CFD) analyses enable a detailed examination of the velocity and pressure distributions around these profiles. Interpolation methods enhance the accuracy of simulations by allowing for the precise definition of wing geometry. These methods make it possible to compare different profile types and achieve an optimal aerodynamic design. Accurate geometric representation of airfoil profiles is critically important for achieving reliable aerodynamic predictions in computational fluid dynamics, particularly under low-Reynolds-number flow conditions where pressure-gradient sensitivity and flow separation behavior become highly geometry-dependent. In this study, the aerodynamic behavior of Clark Y, Eppler 205, FX 63-137, NACA series, RAE 2822, and S1223 airfoil sections under low-Reynolds-number (Re≈1×105) conditions was investigated using CFD analyses. It was observed that the leading-edge suction peak became more pronounced in all profiles with increasing angle of attack, while the lift and drag responses exhibited airfoil-dependent variations across the investigated angles of attack. Differences in the lift and drag responses became more pronounced among the investigated profiles at the higher evaluated angles of attack, reflecting their different geometric and aerodynamic characteristics. Hermite interpolation-based geometric modeling, which forms the basis of this study, improved geometric continuity and reduced interpolation-induced surface irregularities, thereby providing a more consistent geometric representation for the subsequent CFD analyses. It should be emphasized that geometric or numerical stability alone does not establish physical aerodynamic accuracy, which requires independent validation against appropriate reference or experimental data. The results indicate the variations in pressure distributions and aerodynamic coefficients across the examined angles of attack, depending on the airfoil profile, specifically, suction performance becomes more pronounced as the angle of attack increases, while lift and drag characteristics vary among the profiles studied, establishing optimized Hermite airfoil profiles as a basis for CFD aerodynamic evaluation under low-Reynolds-number conditions.