TY - GEN
T1 - Application of immersed boundary method with wall injection for solid rocket motor internal flow
AU - Hirose, Takuya
AU - Ogawa, Shinichiro
AU - Sasaki, Daisuke
AU - Fukushima, Yuma
AU - Obayashi, Shigeru
N1 - Funding Information:
This research partly used computational resources of the HPCI system provided by the Institute of Statistical Mathematics through the HPCI System Research project (hp160150). Part of the computational results in this research were obtained using supercomputing resources at Cyberscience Center, Tohoku University. The authors thank Intelligent Light for the granted use of their post-processing software, FieldView.
Publisher Copyright:
© 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2017
Y1 - 2017
N2 - The vortex shedding in combustion chamber of solid rocket motor may lead the pressure oscillations, which deteriorates the rocket motor performance and could even damage the payload. Cartesian mesh CFD solver is expected to accurately predict such vortex flows using higher-order scheme and to treat complicated configurations easily. Therefore, blockstructured Cartesian mesh solver, Building-Cube Method (BCM), is applied to Taylor flow analysis, which is the simplified combustion chamber model of solid rocket. Immersed boundary method is extended to treat the wall injection from the grain surface. The approach is also applied to real grain configuration, and the usefulness for the complicated geometry is validated.
AB - The vortex shedding in combustion chamber of solid rocket motor may lead the pressure oscillations, which deteriorates the rocket motor performance and could even damage the payload. Cartesian mesh CFD solver is expected to accurately predict such vortex flows using higher-order scheme and to treat complicated configurations easily. Therefore, blockstructured Cartesian mesh solver, Building-Cube Method (BCM), is applied to Taylor flow analysis, which is the simplified combustion chamber model of solid rocket. Immersed boundary method is extended to treat the wall injection from the grain surface. The approach is also applied to real grain configuration, and the usefulness for the complicated geometry is validated.
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U2 - 10.2514/6.2017-1944
DO - 10.2514/6.2017-1944
M3 - Conference contribution
AN - SCOPUS:85086059037
SN - 9781624104510
T3 - AIAA Modeling and Simulation Technologies Conference, 2017
BT - AIAA Modeling and Simulation Technologies Conference, 2017
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Modeling and Simulation Technologies Conference, 2017
Y2 - 9 January 2017 through 13 January 2017
ER -