Numerical Study of Wing with Winglets for Different Cant Angle

Abstract

Aircraft having winglets has a good performance of minimizing vortices and improving fuel efficiency compared to the aircraft wing having no winglets. Winglets being a small structure play an important role in reducing the induced drag in aircraft. A comprehensive 3D numerical study has been carried out for Clark Y airfoil to find the lift and drag coefficient for different cant angles over a wide range of Reynolds number or Mach number. The aerodynamic characteristics of lift coefficient, drag coefficient and lift-to-drag ratio are compared and it's miles found that every winglet configuration at a specific Mach variety had special CL,CD,L/D values, indicating that constant winglets do not provideoptimum aircraft performanceat different levels of flight. The numerical effects are demonstrated with available data in literature.