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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 provide optimum aircraft performance at different levels of flight. The numerical effects are demonstrated with available data in the literature.
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