Numerical Investigation of Suction Parameters for Boundary Layer Control on an Airfoil with Gurney Flap

Document Type : Original Article

Authors

1 Department of Mechanical Engineering, Mazandaran University of Science and Technology, Babol, Iran

2 Department of Mechanical Engineering, Babol Noshirvani University of Technology, Babol, Iran

3 Mechanical Engineering Department, Tennessee Tech University, Cookeville, United States

4 Faculty of Engineering Modern Technologies, Amol University of Special Modern Technologies (AUSMT), Amol, Iran

5 Department of Mechanical Engineering, University of Mazandaran, Babolsar, Iran

Abstract

In the present work, the impact of suction and its related parameters, including dimensionless suction velocity, suction angle, and suction length, on controlling the flow over a NACA 0012 airfoil with a Gurney flap have been numerically investigated. The height of the gurney flap is 2% of the cord. The Reynolds number of the flow is 2.1 × 106, which is entirely turbulent. Turbulent flow has been analyzed using the Reynolds stress model (RSM). The suction on the airfoil is modeled as uniform and normal (vertical suction), and the length of the suction area is 3% of the chord length (CHL) (3cm). The suction jet is designed at two angles of 60 and 90 degrees. The results indicate that with the rise of the suction dimensionless velocity, the drag coefficient (CD) decreases. The maximum ratio of forward to backward dimensionless velocity due to suction is one, occurring at a position 2.5% of the chord length (CHL). This indicates that for optimal performance, the jet suction on the airfoil should be positioned at 2.5% of the CHL. The results of this study contribute to the development of a novel method for boundary layer (BL) control, aiming to optimize drag force on airfoils for improved flow management.

Keywords

References

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Contributions of Science and Technology for Engineering
Volume 1, Issue 4
December 2024
Pages 58-72

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History

  • Receive Date: 21 December 2024
  • Revise Date: 07 January 2025
  • Accept Date: 12 January 2025
  • First Publish Date: 12 January 2025
  • Publish Date: 07 March 2025

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