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Experimental Study of Boundary Layer Transition on an Airfoil Induced by Periodically Passing Wake (II) -A Phase-Averaged Characteristic-
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 Title & Authors
Experimental Study of Boundary Layer Transition on an Airfoil Induced by Periodically Passing Wake (II) -A Phase-Averaged Characteristic-
Park, Tae-Chun; Jeon, U-Pyeong; Gang, Sin-Hyeong;
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 Abstract
This paper describes the phenomena of wake-induced transition of the boundary layers on a NACA0012 airfoil using measured phase-averaged data. Especially, the phase-averaged wall shear stresses are reasonably evaluated using the principle of Computational Preston Tube Method. Due to the passing wake, the turbulent patch is generated in the laminar boundary layer on the airfoil and the boundary layer becomes temporarily transitional. The patches propagate downstream with less speed than free-stream velocity and merge with each other at further down stream station, and the boundary layer becomes more transitional. The generation of turbulent patch at the leading edge of the airfoil mainly depends on velocity defects and turbulent intensity profiles of passing wakes. However, the growth and merging of turbulent patches depend on local streamwise pressure gradients as well as characteristics of turbulent patches. In this transition process, the present experimental data show very similar features to the previous numerical and experimental studies. It is confirmed that the two phase-averaged mean velocity dips appear in the outer region of transitional boundary layer for each passing cycle. Relatively high values of the phase-averaged turbulent fluctuations in the outer region indicate the possibility that breakdown occurs in the outer layer not near the wall.
 Keywords
Wake-Induced Transition;Airfoil;Turbulent Patch;Wall Skin-Friction Coefficient;Calmed Region;
 Language
Korean
 Cited by
1.
주기적 통과 후류의 방향과 주파수가 익형 위 비정상 천이경계층에 미치는 영향,강신형;박태춘;전우평;

대한기계학회논문집B, 2002. vol.26. 5, pp.685-694 crossref(new window)
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