Winglet design and analysis for Cessna 152 – A Numerical study 2019-28-0035
During flight an emergent circulatory flow pattern named vortex is observed at wing tips causing induced drag. An approach to reduce this is by implementing winglets. Winglets are small wing-like lifting surfaces, fitted at the tips of some wings, usually with the objective of decreasing trailing vortex drag and thereby increasing the aerodynamic efficiency of the wing. The aim of the project is to design and analyse winglets for Cessna 152 by varying the cant angle and other parameters. A baseline wing model was designed in CATIA V5, correspondingly wings with winglet. Models were designed by means of specific taper ratio, cant angle and sweep angle. A basic comparison of maximum L/D ratio, optimum drag, and stall are evaluated at different mission segments by varying winglet design parameters. In addition, performances of wings, with and without winglets are evaluated using ANSYS FLUENT and finally, as a result, the optimal performance of the winglets is obtained.