Authors: Nicolas Bédon; Marie-Claude Druguet; Pascal Boubert
Addresses: Aix-Marseille Université, CNRS UMR 7343, Laboratoire IUSTI, 5, rue Enrico Fermi – Technopole de Château-Gombert, 13453, Marseille Cedex 13, France ' Aix-Marseille Université, CNRS UMR 7343, Laboratoire IUSTI, 5, rue Enrico Fermi – Technopole de Château-Gombert, 13453, Marseille Cedex 13, France ' Université de Rouen, CNRS UMR 6614, Laboratoire CORIA, Site Universitaire du Madrillet – BP 12, 76801, St Etienne du Rouvray Cedex, France
Abstract: The present study proposes a simple model for simulating radiation of high-temperature gases, with the intention of predicting radiative transfers in hypersonic flows surrounding a spacecraft when it enters a planetary atmosphere. This paper presents the methodology and the physical models implemented in an aerodynamics code to account for those specific heat transfers in the flow past a blunt body entering a CO2 atmosphere. The line-by-line radiation models include the atomic lines of the atoms C and O, and the molecular systems of the molecule CO, in the [100-7,000 nm] range of the radiation spectrum. The radiation transfers are computed according to a ray-tracing method. Analyses are done to understand the radiative behaviour of the high-temperature gases. The cumulated radiative heat fluxes to the surface of the spacecraft are compared to other computed radiative heat transfer results for verification purpose.
Keywords: modelling; aerodynamics code; hypersonic flow; radiative heat flux; Mars atmosphere entry; ray tracing; line-by-line radiation models; radiative fluxes; heat shield; Martian orbiters; radiation; high-temperature gases; spacecraft entry; planetary atmospheres; heat transfer; blunt body.
International Journal of Aerodynamics, 2014 Vol.4 No.3/4, pp.154 - 174
Available online: 20 Feb 2015 *Full-text access for editors Access for subscribers Purchase this article Comment on this article