Comparative CFD Analysis Of ONERA M6, NACA 0012 And Tapered Finite Wings

A comprehensive comparative computational fluid dynamics (CFD) investigation is presented, analyzing three representative wing configurations: the transonic ONERA M6 benchmark wing, a finite wing based on the symmetric NACA 0012 airfoil section, and a tapered finite wing evaluated at low subsonic speeds. The primary objective is to examine benchmark-oriented transonic flow prediction capabilities and evaluate low-speed finite-wing performance parameters within a unified aerodynamic framework. For the ONERA M6 configuration, the flow field is simulated under the standard validation conditions of a Mach number of 0.8395, an angle of attack of 3.06°, and a Reynolds number of $11.72 \\\\times 10^6$ based on the mean aerodynamic chord. For the low-speed wings, integrated aerodynamic loads at a free-stream velocity of 50 m/s are utilized to determine the aerodynamic coefficients and efficiency trends across various angles of attack. The CFD solver successfully reproduces the expected transonic pressure redistribution, including the characteristic shock-dominated flow structure over the ONERA M6 wing. In the low-speed analysis, the rectangular NACA 0012 wing achieves its maximum aerodynamic efficiency near an 8° angle of attack, whereas the tapered wing exhibits superior aerodynamic efficiency at low angles but suffers a more rapid degradation at higher incidences due to accelerated drag growth. This study effectively consolidates benchmark computational validation, finite-wing aerodynamic theory, and comparative performance analysis.