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Numerical investigation of on-demand fluidic winglet aerodynamic performance and turbulent characterization of a low aspect ratio wing

  • A. Mondal (Department of Aerospace Engineering and Applied Mechanics, Indian Institute of Engineering Science & Technology) ;
  • S. Chatterjee (Department of Aerospace Engineering and Applied Mechanics, Indian Institute of Engineering Science & Technology) ;
  • A. McDonald Tariang (Department of Aerospace Engineering and Applied Mechanics, Indian Institute of Engineering Science & Technology) ;
  • L. Prince Raj (Department of Aerospace Engineering and Applied Mechanics, Indian Institute of Engineering Science & Technology) ;
  • K. Debnath (Department of Aerospace Engineering and Applied Mechanics, Indian Institute of Engineering Science & Technology)
  • Received : 2022.10.05
  • Accepted : 2023.01.05
  • Published : 2023.03.25
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Abstract

Drag reduction is significant research in aircraft design due to its effect on the cost of operation and carbon footprint reduction. Aircraft currently use conventional solid winglets to reduce the induced drag, adding extra structural weight. Fluidic on-demand winglets can effectively reduce drag for low-speed flight regimes without adding any extra weight. These utilize the spanwise airflow from the wingtips using hydraulic actuators to create jets that negate tip vortices. This study develops a computational model to investigate fluidic on-demand winglets. The well-validated computational model is applied to investigate the effect of injection velocity and angle on the aerodynamic coefficients of a rectangular wing. Further, the turbulence parameters such as turbulent kinetic energy (TKE) and turbulent dissipation rate are studied in detail at various velocity injections and at an angle of 30°. The results show that the increase in injection velocity shifted the vortex core away from the wing tip and the increase in injection angle shifted the vortex core in the vertical direction. Further, it was found that a 30° injection is efficient among all injection velocities and highly efficient at a velocity ratio of 3. This technology can be adopted in any aircraft, effectively working at various angles of attack. The culmination of this study is that the implementation of fluidic winglets leads to a significant reduction in drag at low speeds for low aspect ratio wings.

Keywords

References

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