This paper presents the measured mean flow and Reynolds stresses results, obtained on the center-line plane of the airfoil, covering the boundary layers over the upper surface, the potential flow region and the wake downstream of the trailing edge, at αa = 20°. The flying X-hot-wire probe was used to measure mean velocity and turbulence structure over the airfoil. An improved understanding of the physical characteristics of separation on the airfoil sections and in the region of the trailing edge is of direct value for the improvement of high lift wings for aircraft. From the study of the separation flow at angle of attack αa = 20°, the following can be concluded: A stable separation bubble has developed near the trailing edge of the airfoil, covering around 0.6c of the airfoil surface. Also it is found that values of the Reynolds normal and shear stresses move away from the surface with downstream distance, showing turbulence diffusion to be more evident in this flow. In the wake region, relatively large values of Reynolds stresses occurred, which were related to the vertical oscillations in the upper wake.
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ASME 2002 Joint U.S.-European Fluids Engineering Division Conference
July 14–18, 2002
Montreal, Quebec, Canada
Conference Sponsors:
- Fluids Engineering Division
ISBN:
0-7918-3615-0
PROCEEDINGS PAPER
Experimental Investigation of Turbulent Flow With Separation Over a NACA 4412 Airfoil at Angle of Attack 20 Degree Available to Purchase
Omar O. Badran,
Omar O. Badran
Al-Balqa’ Applied University, Amman, Jordan
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Hans H. Bruun
Hans H. Bruun
University of Bradford, Bradford, UK
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Omar O. Badran
Al-Balqa’ Applied University, Amman, Jordan
Hans H. Bruun
University of Bradford, Bradford, UK
Paper No:
FEDSM2002-31067, pp. 21-28; 8 pages
Published Online:
February 24, 2009
Citation
Badran, OO, & Bruun, HH. "Experimental Investigation of Turbulent Flow With Separation Over a NACA 4412 Airfoil at Angle of Attack 20 Degree." Proceedings of the ASME 2002 Joint U.S.-European Fluids Engineering Division Conference. Volume 1: Fora, Parts A and B. Montreal, Quebec, Canada. July 14–18, 2002. pp. 21-28. ASME. https://doi.org/10.1115/FEDSM2002-31067
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