The lift on an airfoil in a turbulent boundary layer 11

Narasimha, R and Kumar, Kishore S (1986) The lift on an airfoil in a turbulent boundary layer 11. Technical Report. National Aeronautical Laboratory, Bangalore, India.

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    This report is a continuation of an earlier study (Kumar13; and Narasimha 1986) on the lift and pitching moment experienced by an airfoil placed within a turbulent boundary layer. The mean velocity in the turbulent boundary layer is represented in this report by a composite profile including the wall and wake laws with a slope that vanishes at the edge of the boundary layer. Results with this composite profile agree qualitatively with those of the one-seventh power law; profile investigated earlier, the maximum difference quantitatively being 22% in the lift coefficient at a blade height of 0.66 boundary layer thickness 6, and 47% in the pitching moment at a blade height of 0.6 delta.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Composite profile;One-seventh power law profile;Shear;Lift
    Subjects: ENGINEERING > Fluid Mechanics and Thermodynamics
    AERONAUTICS > Aerodynamics
    Division/Department: Fluid Dynamics, Fluid Dynamics
    Depositing User: Mr. Ravikumar R
    Date Deposited: 25 Sep 2006
    Last Modified: 24 Aug 2015 14:11

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