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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, E Raynaud and P Tran
Proceedings of the 51st American Institute of Aeronautics and Astronautics Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, pp.15820-15828
American Institute of Aeronautics and Astronautics (AIAA) Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 51st (Grapevine, United States, 07-Jan-2013–10-Jan-2013)
Curran Associates Inc.
2013
url
http://www.proceedings.com/17941.htmlView
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Abstract

aerospace sciences aeronautics astronautics
The prediction of the nonequilibrium radiative heat flux experienced by a spacecraft during Earth 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. The selected conditions 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 electron concentration was inferred from Stark-broadened atomic lines of N and Hα. The post-shock intensity profile was compared to the prediction of the collisional-radiative model. It was shown that the observed nonequilibrium peak was governed by heavy particle impact excitation processes. © 2013 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

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