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<p>The objective of this paper is to effectively control the boundary layer of an aircraft wing using the combination of injection and vortex generator methods. The mass flow, along with the optimum location of injection and vortex generator, is investigated numerically to obtain the performance by calculating the lift and drag coefficient parameters with various angles of attack. The Reynolds Average Navier–Stokes equation is used with the turbulence model of k-epsilon method for this entire study. The results show that the optimum injection location at 20% with the VG location at 60%, along with mass flow, improves the performance of a wing at subsonic speed. The lift coefficient is improved by 42% with the decrement of drag coefficient by 44%. The unique aspect of this work is the combination of boundary layer control methods to pinpoint the best location for active and passive mechanisms and optimize mass flow, all aimed at improving overall performance. The proposed mechanism can be used for any type of currently used or future-based aircraft wings to improve performance.</p>

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Investigation of the Combined Injection and Vortex Generator Method for Aerofoil Performance Enhancement

  • 期刊论文

  • 发表日期：

    2025年8月28日

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  • Divyanshi Nayak,
  • Sandeep Jamkatel,
  • Balaji K,
  • Akhil CK,
  • Patel Ankitkumar Rameshbhai,
  • S. Saranya

摘要

The objective of this paper is to effectively control the boundary layer of an aircraft wing using the combination of injection and vortex generator methods. The mass flow, along with the optimum location of injection and vortex generator, is investigated numerically to obtain the performance by calculating the lift and drag coefficient parameters with various angles of attack. The Reynolds Average Navier–Stokes equation is used with the turbulence model of k-epsilon method for this entire study. The results show that the optimum injection location at 20% with the VG location at 60%, along with mass flow, improves the performance of a wing at subsonic speed. The lift coefficient is improved by 42% with the decrement of drag coefficient by 44%. The unique aspect of this work is the combination of boundary layer control methods to pinpoint the best location for active and passive mechanisms and optimize mass flow, all aimed at improving overall performance. The proposed mechanism can be used for any type of currently used or future-based aircraft wings to improve performance.