Commenced in January 2007
Paper Count: 30124
Hypersonic Flow of CO2-N2 Mixture around a Spacecraft during the Atmospheric Reentry
Abstract:The aim of this work is to analyze a flow around the axisymmetric blunt body taken into account the chemical and vibrational nonequilibrium flow. This work concerns the entry of spacecraft in the atmosphere of the planet Mars. Since the equations involved are non-linear partial derivatives, the volume method is the only way to solve this problem. The choice of the mesh and the CFL is a condition for the convergence to have the stationary solution.
Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1314811Procedia APA BibTeX Chicago EndNote Harvard JSON MLA RIS XML ISO 690 PDF Downloads 502
 A. Goudjo, J.A. Désidéri, “A finite volume scheme to resolution an axisymmetric Euler equations,” Research report INRIA 1005, 1989.
 R. Haoui, A. Gahmousse, D. Zeitoun, “Chemical and vibrational nonequilibrium flow in a hypersonic axisymmetric nozzle,” International Journal of Thermal Sciences, article n° 8, volume 40, (2001), pp787-795.
 R. Haoui, “Finite volumes analysis of a supersonic non-equilibrium flow around the axisymmetric blunt body,” International Journal of Aeronautical and Space Sciences, 11(2), (2010), pp59-68.
 R. Haoui, A. Gahmousse, D. Zeitoun, “ Condition of convergence applied to an axisymmetric reactive flow (Condition de convergence appliquée à un écoulement réactif axisymétrique),” 16th CFM, n°738, Nice, France, 2003.
 K. A Hoffmann, “Computational fluid dynamics for engineers, «Volume II” Library of congress Catalog, March 1995, ISBN 0-9623731-8-4.
 B. Van Leer, “Flux Vector Splitting for the Euler Equations,” Lecture Notes in Physics. 170, (1982), 507-512.