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Aerothermodynamic data of Mars aerocapture by JONATHAN

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JAXA Supercomputer System Annual Report April 2018-March 2019 Report Number: R18EA1402 Subject Category: Aeronautical Technology PDF Responsible Representative: Takashi Ozawa, Research and Development Directorate, Research Unit II Contact Information: Takashi Ozawa(takashi@chofu.jaxa.jp) Members: Toshiyuki Suzuki, Takashi Ozawa, Ryotaro Murakami Abstract To obtain aerothermodynamic data of Mars aerocapture. Reference URL N/A Reasons for using JSS2 It is necessary to use JONATHAN. Achievements of the Year Heat flux distribution around aeroshell was obtained by JONATHAN. As a result, heat flux at stagnation point・・・<<read more>>

Research on the performance improvement of practical aero-engine fuel injector

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JAXA Supercomputer System Annual Report April 2018-March 2019 Report Number: R18EA0730 Subject Category: Aeronautical Technology PDF Responsible Representative: Takashi Yamane, Aeronautical Technology Directorate, En-Core Pre-project team Contact Information: Kazuaki Matsuura, Japan Aerospace Exploration Agency, Aeronautical Technology Directorate, En-Core Pre-project team(matsuura.kazuaki@jaxa.jp) Members: Kazuaki Matsuura, Mitsumasa Makida, Naoki Nakamura, Jun Iino, Huilai Zhang, Kinya Saito, Kunihiko Sakata, Asuka Akino Abstract Our study is focusing on the improvement of fuel injector performance. Numerical simulations on air-flow, atomization, fuel/air mixing, combustion, and thermal analysis・・・<<read more>>

Investigation of internal flow of aircraft combustor for En-Core Project.

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JAXA Supercomputer System Annual Report April 2018-March 2019 Report Number: R18EA0714 Subject Category: Aeronautical Technology PDF Responsible Representative: Mitsumasa Makida(JAXA, Aeronautical Technology Directorate) Contact Information: Mitsumasa Makida(JAXA, Aeronautical Technology Directorate)(makida.mitsumasa@jaxa.jp) Members: Mitsumasa Makida, Naoki Nakamura, Takashi Ishiyama Abstract In the development process of aircraft combustors, air mass flow distribution between fuel nozzles, dilution and cooling air holes on the liner effects performances of combustors. So it is important to understand the internal flow and estimate the mass flow distribution. In・・・<<read more>>

Next generation jet engine technology - development of high efficiency compressor design tecnology and aerodynamic performance prediciton -

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JAXA Supercomputer System Annual Report April 2018-March 2019 Report Number: R18EA0711 Subject Category: Aeronautical Technology PDF Responsible Representative: Toshio Nishizawa, Aeronautical Technology Directorate, Propulsion Research Unit Contact Information: Junichi Kazawa, Aeronautical Technology Directorate, Propulsion Research Unit(kazawa.junichi@jaxa.jp) Members: Junichi Kazawa, Yuntae Lee, Takafumi Kanayama, Kenshi Yamashita, Shunji Enomoto, Susumu Teramoto Abstract We will develop aerodynamic performance improvement technology and high precision aerodynamic performance prediction technology for multistage-compressore assuming an increase in relative tip clearance, corresponding to a small core engine applied・・・<<read more>>

Numerical Plasma Simulation on Advanced Space Propulsion Systems

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JAXA Supercomputer System Annual Report April 2018-March 2019 Report Number: R18EU0904 Subject Category: Space and Astronautical Science PDF Responsible Representative: Ikkoh Funaki, Associate Professor, ISAS Contact Information: Ikkoh Funaki(funaki.ikkoh@jaxa.jp) Members: Shitan Tauchi, Hiroyuki Arai, Ryota Hara Abstract Due to the limitation of the existing spacecraft technology level, it is very difficult to enable solar system explorations in a quick and cost-effective mannger. Objective of this study is to obtain a breakthrough spacecraft propulsion technology that enables solar system exploration of・・・<<read more>>