JAXA Supercomputer System Annual Report February 2022-January 2023 Report Number: R22EDA201G10 Subject Category: Aeronautical Technology PDF Responsible Representative: Kazuyuki Nakakita, Aviation Technology Directorate, Aircraft Lifecycle Innovation Hub Contact Information: Kazuyuki Nakakita, Aviation Technology Directorate, Aircraft Lifecycle Innovation Hub(nakakita.kazuyuki@jaxa.jp) Members: Kuniyuki Takekawa, Takahiro Yamamoto Abstract Aerodynamic characteristics of a fundamental wing-body configuration model was analyzed by CFD to compare with High-Reynolds number wind tunnel data conducted in JAXA's collabollation research. Reference URL N/A Reasons and benefits of using JAXA Supercomputer System・・・<<read more>>
JAXA Supercomputer System Annual Report February 2022-January 2023 Report Number: R22EDA201G19 Subject Category: Aeronautical Technology PDF Responsible Representative: Takashi Aoyama, Aviation Technology Directorate, Program Director Contact Information: Kenichi Kubota, Aircraft Lifecycle Innovation Hub, Aviatoin Technology Directorate(kubota.kenichi@jaxa.jp) Members: Kenichi Kubota, Keita Nakamoto Abstract The purpose of this research is to obtain the simulation technology of particle simulation, known to be useful for analysing multi-physics phenomena, to accelerate aircraft development. Reference URL N/A Reasons and benefits of using JAXA Supercomputer System JSS3・・・<<read more>>
JAXA Supercomputer System Annual Report February 2022-January 2023 Report Number: R22EDA201D01 Subject Category: Aeronautical Technology PDF Responsible Representative: Masashi Harada, AviationTechnology Directorate, Aviation Safety Innovation Hub Contact Information: Masashi Harada(harada.masashi@jaxa.jp) Members: Hirokazu Higashida, Masashi Harada, Junichi Kazawa, Hideji Saiki Abstract Development of Propeller and Ducted Fan Design Tools to Maximize the Static Thrust Reference URL N/A Reasons and benefits of using JAXA Supercomputer System Verification of propeller performance designed with a propeller design tool that maximizes the static thrust. Calculation・・・<<read more>>