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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