TY - GEN
T1 - Simulation of hymets flowfield around baby-sprite entry probe
AU - Diaz, Patricia Ventura
AU - Yoon, Seokkwan
AU - Panerai, Francesco
AU - Mansour, Nagi N.
N1 - Funding Information:
This work is supported by the NASA STMD Entry System Modeling Project (PM: Michael Wright; PI: Michael Barnhardt). Authors thank Jeffrey Hill, Dinesh Prabhu, Chun Tang, and David Saunders for helpful discussions.
Publisher Copyright:
© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2019
Y1 - 2019
N2 - Arc-jets are unique facilities used in research, development, and evaluation of hightemperature thermal protection systems for hypersonic vehicles and planetary entry systems. Thermochemical non-equilibrium computational fluid dynamics simulations have been carried out for the Hypersonic Materials Environmental Test System arc-jet facility to determine the size of a capsule model before arcjet testing by better understanding of the physical phenomena. The results show the effect of the test article geometry and the importance of high-quality grids for accurate solutions. Accurate computational modeling of hypersonic flow fields inside arc-jets under simulated planetary entry conditions would help improve the design of thermal protection systems that may enable human exploration of the Moon, Mars, and beyond.
AB - Arc-jets are unique facilities used in research, development, and evaluation of hightemperature thermal protection systems for hypersonic vehicles and planetary entry systems. Thermochemical non-equilibrium computational fluid dynamics simulations have been carried out for the Hypersonic Materials Environmental Test System arc-jet facility to determine the size of a capsule model before arcjet testing by better understanding of the physical phenomena. The results show the effect of the test article geometry and the importance of high-quality grids for accurate solutions. Accurate computational modeling of hypersonic flow fields inside arc-jets under simulated planetary entry conditions would help improve the design of thermal protection systems that may enable human exploration of the Moon, Mars, and beyond.
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U2 - 10.2514/6.2019-3262
DO - 10.2514/6.2019-3262
M3 - Conference contribution
AN - SCOPUS:85092366804
SN - 9781624105890
T3 - AIAA Aviation 2019 Forum
SP - 1
EP - 19
BT - AIAA Aviation 2019 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Aviation 2019 Forum
Y2 - 17 June 2019 through 21 June 2019
ER -