Experimental study of incompressible mean and turbulence flow fields on and behind a symmetric aerofoil

Hebbar, KS (1981) Experimental study of incompressible mean and turbulence flow fields on and behind a symmetric aerofoil. Technical Report. National Aeronautical Laboratory, Bangalore, India.

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    Abstract

    An experimental investigation was conducted at pre-selected streamwise stations in the boundary layer and wake13; of a 12.5% thick, 600 mm chord two-dimensional symmetrical13; aerofoil mounted at zero incidence in a low speed wind tunnel. The chord Reynolds number was one million and the wake measurements extended upto three chord lengths (or nearly 660 trailing edge momentum thicknesses downstream of the trailing edge. Detailed measurements of two-dimensional profiles of static pressure, mean velocity, turbulence intensity and Reynolds shear stress were carried out with conventional pressure probes and hot wire probes. The measurements indicate rapid energization of the boundary layers immediately behind quot;the trailing edge, leading to significant changes in the flow parameters close to the trailing edge. The boundary layers on the two sides of the aerofoil merge slowly and transform into a wake as the sudden disappearance of the wall shear diffuses outward. Further growth and decay of the wake as well as the tendency of the mean flow field and the fluctuating field towards similarity are discussed.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Aerofoil;Turbulence flow fields;Incompressible mean
    Subjects: AERONAUTICS > Aerodynamics
    Division/Department: Aerodynamics
    Depositing User: Mr. Ravikumar R
    Date Deposited: 11 Sep 2006
    Last Modified: 24 May 2010 09:50
    URI: http://nal-ir.nal.res.in/id/eprint/2684

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