TY - GEN
T1 - Numerical investigation of thermal response on external nozzle in supersonic aircraft by exhaust gas
AU - Fujii, Ken
AU - Matsuo, Akiko
AU - Oki, Junichi
AU - Taguchi, Hideyuki
AU - Chiga, Takahiro
AU - Ikeda, Yutaka
N1 - Publisher Copyright:
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2020
Y1 - 2020
N2 - This paper focuses on thermal response in rear part of engine on HIMICO (High Mach Integrated Control experiment). Firstly, pyrolysis reaction of CFRP, which is used in HIMICO as thermal protection system, is modeled from previous experimental data. Comparison between numerical data and experiment data shows good agreement. Secondly, one-dimensional heat transfer analysis with obtained pyrolysis reaction model on the external nozzle is conducted. By comparing with ramjet engine experiment, calculation result is confirmed to be appropriate. Thirdly, in addition to the thermal response analysis, CFD analysis in the rear part of the engine is conducted. Calculation result indicates that ramjet engine combustion test overestimates heat load on external nozzle compared to actual flight condition because of high back pressure.
AB - This paper focuses on thermal response in rear part of engine on HIMICO (High Mach Integrated Control experiment). Firstly, pyrolysis reaction of CFRP, which is used in HIMICO as thermal protection system, is modeled from previous experimental data. Comparison between numerical data and experiment data shows good agreement. Secondly, one-dimensional heat transfer analysis with obtained pyrolysis reaction model on the external nozzle is conducted. By comparing with ramjet engine experiment, calculation result is confirmed to be appropriate. Thirdly, in addition to the thermal response analysis, CFD analysis in the rear part of the engine is conducted. Calculation result indicates that ramjet engine combustion test overestimates heat load on external nozzle compared to actual flight condition because of high back pressure.
UR - http://www.scopus.com/inward/record.url?scp=85091285672&partnerID=8YFLogxK
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U2 - 10.2514/6.2020-3945
DO - 10.2514/6.2020-3945
M3 - Conference contribution
AN - SCOPUS:85091285672
SN - 9781624106026
T3 - AIAA Propulsion and Energy 2020 Forum
SP - 1
EP - 11
BT - AIAA Propulsion and Energy 2020 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Propulsion and Energy 2020 Forum
Y2 - 24 August 2020 through 28 August 2020
ER -