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Simulation of shock tube radiation measurements with a collisional-radiative model
Conference paper   Peer reviewed

Simulation of shock tube radiation measurements with a collisional-radiative model

A Lemal, Carolyn Jacobs, M Y Perrin, C O Laux, A M Brandis, E Raynaud and P Tran
Proceedings of the 43rd American Institute of Aeronautics and Astronautics Thermophysics Conference
American Institute of Aeronautics and Astronautics (AIAA) Thermophysics Conference, 43rd (New Orleans, United States, 25-Jun-2012–28-Jun-2012)
American Institute of Aeronautics and Astronautics, Inc.
2012
DOI: https://doi.org/10.2514/6.2012-2868
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https://doi.org/10.2514/6.2012-2868View
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Abstract

The prediction of the nonequilibrium radiative heat flux experienced by a spacecraft during Earth's re-entry relies on an approach based on a combination of both numerical simulation and ground test experiments. This paper presents an analysis of the equilibrium and nonequilibrium radiation measured in the NASA Ames' Electric Arc Shock Tube (EAST) facility for typical Moon or Mars return conditions. Therefore, the conditions chosen ranged from 10.54 to 11.17 km/s with a free-stream pressure of 0.1 Torr. The observed emitting spectral features, atomic lines of nitrogen and oxygen, present in the Vacuum Ultraviolet (VUV) and Near-Infrared (NIR) were analyzed. The populations of the emitting states were inferred and compared with predictions obtained from a collisional-radiative model and with simulations obtained with a multi-temperature Boltzmann model. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

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