Winglet Design and Vortex Mitigation in Fixed-Wing Aircraft26
Session Number
1
Advisor(s)
Dr. Tommy Sebastian, MIT Lincoln Laboratory
Location
A117
Discipline
Engineering
Start Date
15-4-2026 10:15 AM
End Date
15-4-2026 11:00 AM
Abstract
Induced drag, generated by wingtip vortices, accounts for approximately 40% of total drag on commercial aircraft during cruise conditions, representing a significant target for aerodynamic optimization. This study investigates how different winglet geometries affect wingtip vortex formation and induced drag in fixed-wing aircraft. Using CAD software, a baseline wing and three winglet configurations (classic vertical, blended, and split-scimitar) were modeled with systematically varied geometric parameters including cant angle, sweep, height, and tip shape. Each model was analyzed using computational fluid dynamics (CFD), solving the Reynolds-averaged Navier-Stokes equations to simulate pressure distributions, velocity fields, and vortex structures across comparable flight conditions. Lift-to-drag ratios and tip vortex strength were quantified for each configuration to enable direct performance comparisons. Prior research suggests that optimized winglets can reduce induced drag by up to 20%, though performance varies significantly by geometry. This project aims to identify which winglet design produces the greatest reduction in induced drag and to illuminate the physical mechanisms underlying winglet effectiveness, contributing to the broader understanding of aerodynamic efficiency in fixed-wing aircraft design.
Winglet Design and Vortex Mitigation in Fixed-Wing Aircraft26
A117
Induced drag, generated by wingtip vortices, accounts for approximately 40% of total drag on commercial aircraft during cruise conditions, representing a significant target for aerodynamic optimization. This study investigates how different winglet geometries affect wingtip vortex formation and induced drag in fixed-wing aircraft. Using CAD software, a baseline wing and three winglet configurations (classic vertical, blended, and split-scimitar) were modeled with systematically varied geometric parameters including cant angle, sweep, height, and tip shape. Each model was analyzed using computational fluid dynamics (CFD), solving the Reynolds-averaged Navier-Stokes equations to simulate pressure distributions, velocity fields, and vortex structures across comparable flight conditions. Lift-to-drag ratios and tip vortex strength were quantified for each configuration to enable direct performance comparisons. Prior research suggests that optimized winglets can reduce induced drag by up to 20%, though performance varies significantly by geometry. This project aims to identify which winglet design produces the greatest reduction in induced drag and to illuminate the physical mechanisms underlying winglet effectiveness, contributing to the broader understanding of aerodynamic efficiency in fixed-wing aircraft design.