Please use this identifier to cite or link to this item: http://nopr.niscair.res.in/handle/123456789/29714
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dc.contributor.authorMehta, R C-
dc.contributor.authorSastry, M S-
dc.date.accessioned2014-11-05T09:23:18Z-
dc.date.available2014-11-05T09:23:18Z-
dc.date.issued1997-04-
dc.identifier.issn0975-1017 (Online); 0971-4588 (Print)-
dc.identifier.urihttp://hdl.handle.net/123456789/29714-
dc.description41-48en_US
dc.description.abstractThe time-dependent compressible, axisymmetric Euler equations are solved using fifth stage Runge- Kutta time-stepping method to obtain flow field over a typical heat shield of the satellite launch vehicle. The local normal load distributions, normal force coefficient and centre of pressure are calculated using tangent-cone method in conjunction with the numerically computed pressure variation. The present hybrid scheme can be easily employed to obtain preliminary design of the heat shield before it can be simulate in the wind-tunnel facility. Numerical results of the present analysis are compared with the available experimental data, and found in good agreement between them.en_US
dc.language.isoen_USen_US
dc.publisherNISCAIR-CSIR, Indiaen_US
dc.rights CC Attribution-Noncommercial-No Derivative Works 2.5 Indiaen_US
dc.sourceIJEMS Vol.04(2) [April 1997]en_US
dc.titleComputation of aerodynamic load and coefficient for satellite launch vehicleen_US
dc.typeArticleen_US
Appears in Collections:IJEMS Vol.04(2) [April 1997]

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