Determination of the radiative emission of a hypersonic flow simulating the Cassini-Titan atmospheric entry probe environment

Details Determination of the radiative emission of a hypersonic flow simulating the Cassini-Titan atmospheric entry probe environment Determination of the radiative emission of a hypersonic flow simulating the Cassini-Titan atmospheric entry probe environment

Jun 1990

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1990fdpd.conft....p&link_type=abstract

AIAA, Fluid Dynamics, Plasma Dynamics and Lasers Conference, 21st, Seattle, WA, June 18-20, 1990. 11 p.

Other

Aerothermochemistry, Atmospheric Entry Simulation, Hypersonic Flow, Radiative Heat Transfer, Satellite Atmospheres, Titan, Chemical Equilibrium, Nonequilibrium Thermodynamics, Oblique Shock Waves, Shock Layers

Scientific paper

The joint ESA-NASA Cassini mission includes the Huygens probe, which will penetrate the atmosphere of the Saturn moon Titan at around 5 km/sec. The radiative configuration of the shock layer is of a special interest because of the peculiar composition of the atmosphere and because non-equilibrium conditions are present over part of the trajectory: with the result that radiative heat transfer should be taken into account in the design of the heat shield. The present paper is a first report in which concentration of major species and values of thermophysical variables were computed as a function of distance behind a normal shock traveling at 5 km/sec into a simulated Titan atmosphere. A three temperature model was used with a suitable choice of chemical reactions among several species, and the associated rate constants.

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