TY - GEN
T1 - An expedient for alleviating aerodynamic heating and drag on capsule forward heat shield
AU - Morimoto, Naoki
AU - Yamashita, Jun
AU - Aso, Shigeru
AU - Tani, Yasuhiro
N1 - Publisher Copyright:
© 2015 by the American Institute of Aeronautics and Astronautics, Inc.
PY - 2015
Y1 - 2015
N2 - Numerical investigations on the feasibility of the opposing jet through the extended nozzle applied to a forward heat shield of reentry capsule are reported. In the present CFD analyses, free stream condition was Mach 6.6. The test results show that this new device reduces both aerodynamic heating and aerodynamic drag on forward heat shield up to 90% and 91%, respectively. These results strongly suggest that this new device is one of the promising thermal protection systems for future supersonic and hypersonic flight vehicles.
AB - Numerical investigations on the feasibility of the opposing jet through the extended nozzle applied to a forward heat shield of reentry capsule are reported. In the present CFD analyses, free stream condition was Mach 6.6. The test results show that this new device reduces both aerodynamic heating and aerodynamic drag on forward heat shield up to 90% and 91%, respectively. These results strongly suggest that this new device is one of the promising thermal protection systems for future supersonic and hypersonic flight vehicles.
UR - http://www.scopus.com/inward/record.url?scp=84980373406&partnerID=8YFLogxK
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U2 - 10.2514/6.2015-2080
DO - 10.2514/6.2015-2080
M3 - Conference contribution
AN - SCOPUS:84980373406
SN - 9781624103438
T3 - 53rd AIAA Aerospace Sciences Meeting
BT - 53rd AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 53rd AIAA Aerospace Sciences Meeting, 2015
Y2 - 5 January 2015 through 9 January 2015
ER -