Atsushi Hashimoto

J-GLOBAL         Last updated: Nov 16, 2018 at 10:44
 
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Name
Atsushi Hashimoto
Research funding number
30462899
ORCID ID
0000-0003-4428-0406

Research Interests

 
 

Research Areas

 
 

Published Papers

 
Tsukasa Nagao, Atsushi Hashimoto, Tetsuya Sato
AIAA Aerospace Sciences Meeting, 2018      Jan 2018
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. The convergence and accuracy of gradient values on high aspect ratio grids remain problems in CFD. One of the methods solving these problems is to use a hyp...
Yoimi Kojima, Atsushi Hashimoto, Masaharu Kameda
AIAA Aerospace Sciences Meeting, 2018      Jan 2018
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. Open cavity in transonic flow is a common flow field in aeronautical engineering. Prediction of flow field over the cavity is still challenging due to its m...
Atsushi Hashimoto, Takashi Ishida, Yuya Ohmichi, Takashi Aoyama, Takashi Yamamoto, Kenji Hayashi
AIAA Aerospace Sciences Meeting, 2018      Jan 2018
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. Predicting a transonic buffet over an aircraft is one of the challenging problems for the current CFD community due to the unsteady shock/boundary layer int...
Hidekazu Yoshida, Tsukasa Nagao, Akira Sato, Sho Wakabayashi, Tetsuya Sato, Atsushi Hashimoto, Takashi Aoyama, Takayuki Kojima
53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017      Jan 2017
This paper presents a numerical analysis on the air intake of HIMICO (High-Mach Integrated Control experiment). Mass capture ratio (MCR) of the intake in the supersonic wind tunnel test is different from that we analytically expected quantitativel...
Ohmichi Y, Ishida T, Hashimoto A.
AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting      2017   [Refereed]
Kitamura K, Hashimoto A.
Journal of Computational Physics   341 313-340   2017   [Refereed]
Ito Y, Murayama M, Hashimoto A, Ishida T, Yamamoto K, Aoyama T, Tanaka K, Hayashi K, Ueshima K, Nagata T, Ueno Y, Ochi A.
AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting      2017   [Refereed]
Ishida T, Hashimoto A, Ohimichi Y, Aoyama T, Yamamoto T, Takekawa K.
AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting      2017   [Refereed]
Hashimoto A, Murakami K, Aoyama T, Tagai R, Koga S, Nagai S, Hayashi K.
54th AIAA Aerospace Sciences Meeting      2016   [Refereed]
Kitamura K, Hashimoto A
Computers and Fluids   126 41-57   2016   [Refereed]

Misc

 
橋本 敦, 石田 崇, 村上 桂一, 青山 剛史, 菱田 学
年会講演会講演集   49    Apr 2018
HASHIMOTO Atsushi
Aeronautical and Space Sciences Japan   66(8) 254-254   2018
吉本 稔, 石田 崇, 橋本 敦, 青山 剛史
三菱重工技報 = Mitsubishi Juko giho   55(2) 63-67   2018
小島良実, 小島良実, 橋本敦, 青山剛史, 亀田正治
日本航空宇宙学会論文集   66(1) 39‐45(J‐STAGE)   2018
上島啓司, 菅原瑛明, 石田崇, 橋本敦, 口石茂, 青山剛史
飛行機シンポジウム講演集(CD-ROM)   55th ROMBUNNO.1D01   2017
橋本敦, 青山剛史, 上野真, 中北和之, 浜本滋, 澤田恵介, 松島紀佐, 今村太郎, 越智章生, 吉本稔
飛行機シンポジウム講演集(CD-ROM)   55th ROMBUNNO.3A16   2017
東貴弘, 大道勇哉, 小島良実, 橋本敦, 高橋孝, 稲田喜信
数値流体力学シンポジウム講演論文集(CD-ROM)   31st ROMBUNNO.A01‐1   2017
小島良実, 橋本敦, 亀田正治
飛行機シンポジウム講演集(CD-ROM)   55th ROMBUNNO.3D02   2017
吉田秀和, 長尾志, 佐藤哲也, 牧野好和, 上野篤史, 橋本敦
飛行機シンポジウム講演集(CD-ROM)   55th ROMBUNNO.3A06   2017
橋本敦, 石田崇, 青山剛史, 山本貴弘, 林謙司, 上島啓司
飛行機シンポジウム講演集(CD-ROM)   55th ROMBUNNO.3A11   2017

Research Grants & Projects

 
Ministry of Education, Culture, Sports, Science and Technology: Grants-in-Aid for Scientific Research(挑戦的萌芽研究)
Project Year: 2011 - 2013    Investigator(s): Shigeru SUNADA
We have proposed a 'Split wing', which is composed of some square wings. 'Split wing' has two types. One is the 'Slide type' and the other is the 'Slit type'. In the former type, the distances between the square wings are varied by sliding them al...
Ministry of Education, Culture, Sports, Science and Technology: Grants-in-Aid for Scientific Research(基盤研究(B))
Project Year: 2011 - 2013    Investigator(s): Shigeru SUNADA
In oreder to develop a propeller of a Mars airplane, the characteristics of a propeller operating at a Reynolds number with the order of 1000 and a high Mach number (Mach number at tip is about 0.5) were investigated by experiments at three wind t...