Please use this identifier to cite or link to this item: http://nopr.niscair.res.in/handle/123456789/29795
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dc.contributor.authorMehta, R C-
dc.contributor.authorPrasad, J K-
dc.date.accessioned2014-11-07T06:55:06Z-
dc.date.available2014-11-07T06:55:06Z-
dc.date.issued1996-08-
dc.identifier.issn0975-1017 (Online); 0971-4588 (Print)-
dc.identifier.urihttp://hdl.handle.net/123456789/29795-
dc.description141-147en_US
dc.description.abstractNumerical and experimental results on the supersonic free jets issuing from convergent-divergent conical nozzles of different Mach numbers are presented. In the numerical calculations, the two-stage Runge-Kutta time-stepping scheme is applied assuming inviscid and axially symmetric flow while in the experiments, the flow field was visualized using Schlieren photography and static pressures along the centre line of the free jets are measured using static probe. Effects of exit Mach number and expansion ratio on shock-cell structure are studied with the help of Schlieren pictures, isobar contours and velocity vector plot. A linear relationship between shock cell length and β2 is obtained for exit Mach numbers of 2.2, 2.6 and 3.1 and expansion ratio in  the range1.2-0.4.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.03(4) [August 1996]en_US
dc.titleEstimation of shock-cell structure of axisymmetric supersonic free jetsen_US
dc.typeArticleen_US
Appears in Collections:IJEMS Vol.03(4) [August 1996]

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