Numerical Aerodynamic Analysis of the NASA SC(۲)-۰۷۱۴ Supercritical Airfoil Under Transonic Condition

This study presents a computational analysis of the NASA SC(۲)-۰۷۱۴ supercritical airfoil to evaluate its aerodynamic behavior under transonic flow conditions. Using validated Computational Fluid Dynamics (CFD) simulations, the investigation focuses on key aerodynamic parameters including lift, drag, and pitching moment across Mach numbers ranging from ۰.۶۰ to ۰.۸۵ and varying angles of attack. The mesh independence study and application of the Spalart-Allmaras turbulence model ensure high numerical fidelity. Results indicate that the airfoil effectively delays the onset of drag rise and maintains favorable lift characteristics at high subsonic speeds. At a Mach number of ۰.۸۵, the airfoil sustains elevated lift performance over a broad angle of attack range, while exhibiting stable pitching moment behavior. Comparison with experimental data confirms strong agreement in pressure coefficient distributions, reinforcing the reliability of the simulation approach. These findings underscore the aerodynamic efficiency and design resilience of the SC(۲)-۰۷۱۴ airfoil, supporting its suitability for high-performance aircraft applications.

کلیدواژه ها:

CFD ، Supercritical Airfoil ، Transonic Flow ، Numerical Investigation