Numerical Validation of the N3S-NATUR Code for Supersonic Nozzles and Afterbody Flows

Details Numerical Validation of the N3S-NATUR Code for Supersonic Nozzles and Afterbody Flows Numerical Validation of the N3S-NATUR Code for Supersonic Nozzles and Afterbody Flows

Feb 2005

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2005esasp.563..465p&link_type=abstract

Proceedings of the Fifth European Symposium on Aerothermodynamics for Space Vehicles (ESA SP-563). 8-11 November 2004, Cologne,

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Scientific paper

A numerical investigation was conducted to assess the ability of the three-dimensional Navier-Stokes solver, N3S-Natur [1], using the k-ω SST turbulence model when computing nozzle-afterbody flows with propulsive jets. Three nozzle configurations were selected as test cases for the computational method: the first is the ONERA TIC nozzle, the second is an axisymmetric boat-tailed afterbody configuration and the third is a fully 3D transonic nozzle. In most situations, internal and external flow-field regions are modeled. The obtained results are carefully analyzed and compared to the experimental data. A three-dimensional computation was done to make evidence of 3D phenomena which are not negligible. A particular attention was payed to the appearance of a recirculation zone on the afterbody.

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