• S. Pravinkumar
• Gutlapalli Virinchi Hrushikesa Koumudi
• S. Joyson Abraham
• G. Gifta Jerith
• J. Ebenezer Samuel Daniel

Wingtip vortices generated by finite-span wings are a primary source of induced drag, aerodynamic inefficiency, transonic shock formation, and unsteady structural loading in modern transport aircraft. The implementation of advanced wingtip devices has become an effective approach for enhancing aerodynamic performance while simultaneously improving structural stability and fuel efficiency. This study presents a comprehensive computational comparison of four widely adopted winglet configurations, namely the raked wingtip, wingtip fence, blended winglet, and split scimitar winglet, to evaluate their influence on induced drag reduction, shock wave attenuation, and wingtip vibration suppression. Parametric three-dimensional winglet geometries were developed using a CAD-based modelling approach, while aerodynamic flow characteristics were assessed through CFD-style analyses incorporating pressure distribution, Mach number contours, velocity streamlines, turbulent kinetic energy, drag polars, spanwise lift distributions, and wingtip vortex behaviour. The comparative analysis demonstrates that all winglet configurations improve aerodynamic performance relative to the baseline wing; however, their effectiveness varies significantly with geometric design. Among the configurations investigated, the split scimitar winglet exhibits the highest aerodynamic efficiency, achieving an induced drag reduction of approximately 8.9%, a shock strength reduction of nearly 34%, and a wingtip vibration reduction of approximately 33% under the representative operating conditions considered in this study. The blended winglet also provides substantial improvements, whereas the raked wingtip and wingtip fence deliver comparatively moderate aerodynamic benefits. The superior performance of the split scimitar winglet is primarily attributed to its enhanced capability to diffuse and redistribute the wingtip vortex into weaker counter-rotating structures, thereby reducing vortex intensity, minimizing pressure gradients, and alleviating unsteady aerodynamic loading. The findings highlight the importance of winglet geometry in improving aircraft aerodynamic efficiency, reducing structural fatigue, and enhancing overall flight performance. This study provides valuable insights for the aerodynamic design and optimization of future fuel-efficient transport aircraft and establishes a practical framework for subsequent investigations involving high-fidelity computational simulations and experimental validation.

: Aircraft Winglet, Computational Fluid Dynamics (CFD), Induced Drag, Wingtip Vortex, Split Scimitar Winglet, Blended Winglet, Shock Wave Mitigation, Aeroelastic Vibration, Aerodynamic Performance, Transport Aircraft.

"Computational Investigation of Advanced Winglet Configurations for Enhanced Aircraft Aerodynamic Performance", International Journal of Emerging Technologies and Innovative Research (www.jetir.org), ISSN:2349-5162, Vol.13, Issue 9, page no.a568-a582, September-2026, Available :http://www.jetir.org/papers/JETIR2609069.pdf

"Computational Investigation of Advanced Winglet Configurations for Enhanced Aircraft Aerodynamic Performance", International Journal of Emerging Technologies and Innovative Research (www.jetir.org | UGC and issn Approved), ISSN:2349-5162, Vol.13, Issue 9, page no. ppa568-a582, September-2026, Available at : http://www.jetir.org/papers/JETIR2609069.pdf