Performance of an airfoil at low reynolds number

Premalatha, and Ramamoorthy, P (1991) Performance of an airfoil at low reynolds number. Technical Report. National Aeronautical Laboratory, Bangalore, India.

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    Abstract

    A new airfoil performance software is developed by combining two independent codes . The first one is based on Theodorsen's thick airfoil theory and second one is a boundary layer code based on the integral method.13; The lift and pitching moment coefficients are obtained by Theodorsen's theory suitably modified for the viscous effects.The comparison between this code and NCSU code 'and experiments for a few low drag airfoil show good correlation and hence the code has great potential for further development.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Airfoil;Performance
    Subjects: AERONAUTICS > Aeronautics (General)
    Division/Department: Computational and Theoretical Fluid Dynamics Division, Computational and Theoretical Fluid Dynamics Division
    Depositing User: Mr. N A
    Date Deposited: 24 Jun 2006
    Last Modified: 12 Jun 2013 11:02
    URI: http://nal-ir.nal.res.in/id/eprint/1856

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