Drag Reduction Performance of Triangular (V-groove) Riblets with Different Adjacent Height Ratios

Document Type : Regular Article

Authors

1 Faculty of Materials and Manufacturing, Beijing University of Technology, Beijing 100124, China

2 Beijing Key Laboratory of Advanced Manufacturing Technology, Beijing University of Technology, Beijing 100124, China

3 School of Mechanical Engineering, Tianjin University, Tianjin 300072, China

4 Faculty of Materials and Manufacturing, Beijing University of Technology, Beijing 100124, China; Beijing Key Laboratory of Advanced Manufacturing Technology, Beijing University of Technology, Beijing 100124, China

Abstract

Surface structure is used to interfere with the turbulent boundary layer in the groove drag reduction, which is important to the endurance and stability of high-speed and ultrahigh-speed aircraft. The size of the groove structure directly affects the flow in the turbulent boundary layer and changes the drag reduction effect. The drag reduction characteristics of bionic triangular (V-groove) riblets were studied through Particle Image Velocimetry (PIV) experiment and Finite Volume Method (FVM) simulation. Triangular riblets with adjacent height ratios (AHR) of 1.00, 1.74, and 3.02 were considered in this research, and the influence of these groove structures on the flow characteristics of turbulence near the wall is compared with those of the smooth plates. The distribution of time-averaged velocity, turbulence intensity, and coherent structures of turbulent boundary layer on the riblet surface is analyzed to document the effects of the geometric parameters of various groove structures on drag reduction rates. Results showed that the best drag reduction is obtained using the V-groove riblets with adjacent height ratio of 1:1 under the low free-stream velocity. The results can be used as a reference for further optimization of drag reduction structures with surface grooves.

Keywords

References

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History

  • Received: 20 September 2022
  • Revised: 10 December 2022
  • Accepted: 13 December 2022
  • Available online: 01 April 2023

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