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Assessment of Reflected Shock Tunnels for Mars Entry Vehicle Ground Testing

Leibowitz, Matthew G. and Austin, Joanna M. (2018) Assessment of Reflected Shock Tunnels for Mars Entry Vehicle Ground Testing. In: AIAA Scitech 2018 Forum. American Institute of Aeronautics and Astronautics , Reston, VA, Art. No. 2018-1721. ISBN 9781624105241.

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Recent carbon dioxide studies in reflected shock tunnel testing have noted discrepancies in the shock shapes between experiments and simulations. These have been attributed to freezing vibrational modes unaccounted for in the simulations during the rapid expansion through the nozzle. This study focuses on blunt body CO_2 experiments and simulations in the T5 Reflected Shock Tunnel to examine possible sources of error when making standoff distance and heat flux measurements. The effect of increasing the nozzle area ration to further expand the flow in the nozzle is examined and a method for making consistent standoff distance comparisons from experiments and simulations is developed. Finally, experiments and simulations are compared to theoretical models.

Item Type:Book Section
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Austin, Joanna M.0000-0003-3129-5035
Additional Information:© 2018 American Institute of Aeronautics and Astronautics.
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AIAA Paper2018-1721
Record Number:CaltechAUTHORS:20190816-144341084
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Official Citation:Assessment of Reflected Shock Tunnels for Mars Entry Vehicle Ground Testing Matthew G. Leibowitz and Joanna M. Austin 2018 AIAA Aerospace Sciences Meeting.
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:97972
Deposited By: George Porter
Deposited On:20 Aug 2019 22:07
Last Modified:16 Nov 2021 17:35

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