Comparative Analysis of Airfoil-Flap Configurations to Determine Aerodynamic Efficiency in Heavy-Lift Cargo Aircraft

Abstract

Heavy-lift cargo aircraft operate under strict aerodynamic constraints due to high wing loading, large gross weight, and the need to balance low-speed lift with cruise efficiency. This study presents a comparative aerodynamic analysis of NASA Phase-2 supercritical airfoil–flap configurations for heavy-lift cargo aircraft, using the Boeing 757-200F as a representative reference platform. A constraint-based sizing method was first used to establish performance requirements, including wing loading, thrust-to-weight ratio, cruise Mach number, and required maximum lift coefficient. Based on these requirements, three NASA Phase-2 supercritical airfoils, SC (2)-0612, SC (2)-0712, and SC (2)-0714, were selected for comparison because of their transonic suitability and compatibility with high-lift systems. A double-slotted Fowler flap configuration was then adopted to improve take-off and landing performance. Preliminary aerodynamic screening was performed in XFLR5, followed by two-dimensional CFD simulations in ANSYS Fluent using the SST k-ω turbulence model under representative cruise, take-off, and landing conditions. The results show that SC (2)-0612 provides strong cruise efficiency, while SC (2)-0714 with a 10°/20° flap setting offers favorable take-off performance within the analyzed angle-of-attack range. Overall, SC (2)-0714 appears to be the most balanced candidate within the scope of the present sectional 2D CFD study. Beyond the comparative results, this study also provides an integrated preliminary workflow that connects constraint analysis, airfoil selection, flap configuration, XFLR5 screening, and CFD evaluation for heavy cargo aircraft airfoil–flap selection. The results offer sectional design guidance, while future 3D validation is required to capture finite-wing effects.