The flow field around an NACA0012 wing is visualized in a towing tank using particle image velocimetry at a low Reynolds number of 2.0 × 104. A semi-span model of the NACA0012 wing with an aspect ratio of 3.0 is used for the experiment. The visualization is performed at the streamwise cross section along the centerline of the wing model. In the experimental investigation of the turbulence effects, a turbulence grid is installed upstream of the wing model. The turbulence is generated by moving the turbulence grid and the wing model at the same velocity. The effect of turbulence on the flow field is investigated by comparing the results obtained without using the grid. The flow field visualization around the wing model is achieved in a turbulent flow. It is found that turbulence leads to the reattachment of the separated boundary layer on the wing surface.
Influence of Turbulence Intensity on Flow Field Around NACA0012 Wing at Reynolds Number of 20,000
Lect. Notes Electrical Eng.
Asia-Pacific International Symposium on Aerospace Technology ; 2021 ; Korea (Republic of) November 15, 2021 - November 17, 2021
The Proceedings of the 2021 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2021), Volume 1 ; Chapter : 39 ; 505-511
2022-08-31
7 pages
Article/Chapter (Book)
Electronic Resource
English
Transition to turbulence and control in the incompressible flow around a NACA0012 wing
Tema Archive | 2005
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