Computation of Hypersonic Flow Past a Ballistic Re-Entry Module

Saxena, SK and Shailendra Prasad, - (1997) Computation of Hypersonic Flow Past a Ballistic Re-Entry Module. Technical Report. National Aerospace Laboratories, Bangalore, India.

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    Abstract

    The capability of an indigenously developed 3D implicit upwind Reynolds Averaged13; Navier-Stokes Code, called EURANIUM, to provide reliable estimates of aerodynamic13; coefficients and accurate flow field details at hypersonic Mach number for a ballistic13; re-entry configuration for payload recovery is demonstrated. The computed aerodynamic13; coefficients compare well with the hypersonic wind tunnel test data.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Hypersonic;Ballistic re-entry;Reynolds Averaged Navier-Stokes
    Subjects: AERONAUTICS > Aircraft Design, Testing & Performance
    Division/Department: Computational and Theoretical Fluid Dynamics Division, Computational and Theoretical Fluid Dynamics Division
    Depositing User: Mrs Manoranjitha M D
    Date Deposited: 08 May 2006
    Last Modified: 24 May 2010 09:41
    URI: http://nal-ir.nal.res.in/id/eprint/1271

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