An expedient for alleviating aerodynamic heating and drag on capsule forward heat shield

Naoki Morimoto, Jun Yamashita, Shigeru Aso, Yasuhiro Tani

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)

Abstract

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.

Original languageEnglish
Title of host publication53rd AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103438
DOIs
Publication statusPublished - Jan 1 2015
Event53rd AIAA Aerospace Sciences Meeting, 2015 - Kissimmee, United States
Duration: Jan 5 2015Jan 9 2015

Publication series

Name53rd AIAA Aerospace Sciences Meeting

Other

Other53rd AIAA Aerospace Sciences Meeting, 2015
CountryUnited States
CityKissimmee
Period1/5/151/9/15

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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  • Cite this

    Morimoto, N., Yamashita, J., Aso, S., & Tani, Y. (2015). An expedient for alleviating aerodynamic heating and drag on capsule forward heat shield. In 53rd AIAA Aerospace Sciences Meeting [AIAA 2015-2080] (53rd AIAA Aerospace Sciences Meeting). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2015-2080