Study of the effect of pressure gradient on compressible laminar large boundary layers at large prandtl numbers

Gopinath, R and Murthy, AV (1969) Study of the effect of pressure gradient on compressible laminar large boundary layers at large prandtl numbers. Technical Report. National Aeronautical Laboratory, Bangalore, India.

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    Abstract

    An analytical study of the asymptotic behaviour compressible laminar similar boundary layers with preag zadient has been made in this note for larg e Prandtl A sort of hybrid technique which essentially involves -cne use of the method of matched asymptotic expansions for the energy equation and Meksyn' s method for the momentum equation has been made use of in order to solve the coupled momentum and energy equations. Also, exact numerical solutions have been obtained for Prandtl numbers upto thirty and for a pressure gradient parameter .1? = 0.2, for the heat transfer as well as the plate insulated cases by the Newton-Raphson's technique.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Asymptotic behaviour;Skin friction;Pressure gradient;Boundary13; layer
    Subjects: AERONAUTICS > Aeronautics (General)
    Division/Department: Computational and Theoretical Fluid Dynamics Division, Computational and Theoretical Fluid Dynamics Division
    Depositing User: M/S ICAST NAL
    Date Deposited: 12 Dec 2006
    Last Modified: 24 May 2010 09:54
    URI: http://nal-ir.nal.res.in/id/eprint/3712

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