Matsuo, Akiko

写真a

Affiliation

Faculty of Science and Technology, Department of Mechanical Engineering ( Yagami )

Position

Professor

Related Websites

External Links
Scopus Paper Info  
Paper Count: 256 Citation Count: 4193 h-index: 35

Click to view the Scopus page. The data was downloaded from Scopus API in October 04, 2026, via http://api.elsevier.com and http://www.scopus.com .

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Profile Summary 【 Display / hide 】

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Career 【 Display / hide 】

  • 1989.04
    -
    1993.03

    (株)リクルート　スーパーコンピュータ研究所勤務

  • 1992.01
    -
    1993.09

    日本学術振興会（ＤＣ１）（名古屋大学）, 特別研究員

  • 1993.10
    -
    1995.03

    日本学術振興会（ＰＤ）（文部省宇宙科学研究所）, 特別研究員

  • 1995.04
    -
    1997.03

    慶應義塾大学理工学部, 助手

  • 1995.06

    文部科学省宇宙科学研究所, 共同研究員

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Academic Background 【 Display / hide 】

  • 1987.03

    Tsuda College, Faculty of Arts and Science, 数学科

    University, Graduated

  • 1989.03

    Nagoya University, Graduate School, Division of Engineering, 航空工学専攻課程

    Graduate School, Completed, Master's course

  • 1993.09

    Nagoya University, Graduate School, Division of Engineering, 航空工学専攻課程

    Graduate School, Completed, Doctoral course

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Academic Degrees 【 Display / hide 】

  • 工学, Nagoya University, 1993.09

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Research Areas 【 Display / hide 】

  • Manufacturing Technology (Mechanical Engineering, Electrical and Electronic Engineering, Chemical Engineering) / Fluid engineering

  • Frontier Technology (Aerospace Engineering, Marine and Maritime Engineering) / Aerospace engineering

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Books 【 Display / hide 】

  • Detonation Control for Propulsion: Pulse Detonation and Rotating Detonation Engines (Shock Wave and High Pressure Phenomena)

    K. Matsuoka, H. Taki, J. Kasahara, H. Watanabe, A. Matsuo, and T. Endo, Springer International Publishing, 2018.01

    Scope: Pulse Detonation Cycle at Kilohertz Frequency, Chapter 8, pp.183-198

  • Detonation Control for Propulsion: Pulse Detonation and Rotating Detonation Engines (Shock Wave and High Pressure Phenomena)

    J. Kasahara, Y. Kato, K. Ishihara, K. Goto, K. Matsuoka, A. Matsuo, I. Funaki, H. Moriai, D. Nakata, K. Higashino, and N. Tanatsugu, Springer International Publishing, 2018.01

    Scope: Application of Detonation Waves to Rocket Engine Chamber, Chapter 4, pp.61-76

  • 機械工学便覧 基礎編 α5　熱 工 学

    松尾亜紀子　他62名, 日本機械学会, 2006.12

    Scope: 2・14　気体の流動　pp44-48

  • 数値流体力学ハンドブック

    松尾亜紀子　他79名, 丸善, 2003.03

    Scope: 6・6　デトネーション　pp300-303

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Papers 【 Display / hide 】

  • Mushroom-cloud development and transport of radioactive materials and dust: A numerical study of the Nagasaki atomic bombing

    Nakajima K., Matsuo A.

    Progress in Earth and Planetary Science 13 ( 1 )  2026.12

    　View Summary

    In this study, the blast-wave formation and mushroom-cloud development associated with the Nagasaki atomic bombing were numerically investigated to construct initial conditions for subsequent meteorological simulations of “black rain.” To evaluate the three-dimensional transport of hazardous materials within the cloud, two distinct material tracers were treated as passive scalars in an Eulerian framework and solved together with the compressible airflow: bomb-derived radioactive material, assumed to represent plutonium released from the bomb, and ground-derived dust, representing non-radioactive smoke and dust associated with urban fires and disturbed surface materials. The computation was carried out in three stages: a one-dimensional theoretical blast-wave calculation, a high-resolution three-dimensional simulation of the early blast-wave/fireball interaction, and a large-domain three-dimensional simulation of the subsequent mushroom-cloud rise. The numerical results showed that sufficient grid resolution is required in both the blast-wave and mushroom-cloud stages to reproduce the cloud-rise behavior accurately. In the blast-wave stage, coarse grids smeared the reflected-shock/fireball interaction and led to an underestimation of the later cloud-top height. The background atmospheric profile also affected the buoyant rise, and a dry adiabatic atmosphere showed better agreement with historical nuclear-test data than the International Standard Atmosphere. The three-dimensional blast-wave simulation clarified that the reflected shock wave deforms the fireball and induces a strong axial updraft, which provides the initial flow structure for the subsequent mushroom-cloud rise. The mushroom-cloud simulation reproduced the buoyant ascent of the hot fireball, the horizontal spreading of the cloud head, and the development of a vortex-ring structure. The potential-temperature perturbation field visualized the hot core and updraft, while the relative-humidity field indicated possible condensate-cloud formation in the upper part of the cloud. The two solid-phase components exhibited distinct transport behaviors depending on their initial locations. Ground-derived dust was entrained mainly through the central updraft, whereas bomb-derived radioactive material was preferentially incorporated into the vortex-ring region around the cloud head. These results provide the three-dimensional initial distribution of hazardous materials for meteorological simulations of black rain. (Figure presented.)

  • Symmetric, Square, Lattice Pattern Injector Design and Experimental Flow Characterization within a Detonation Engine

    Joseph V., Kasahara J., Matsuoka K., Itouyama N., Yasui M., Ide Y., Matsuo A., Funaki I., Higashino K.

    AIAA Science and Technology Forum and Exposition AIAA Scitech Forum 2026  2026

    　View Summary

    Flow inside a rotating detonation engine (RDE), which is studied for use in aircraft and rocket propulsion, is affected by the geometry of the injector component. Typically, RDEs are cylindrical in nature and have a circular injection pattern. However, although hollow RDEs are now being studied, the injector pattern has remained the fixed-radius, circular injector pattern. In order to understand the impact of uniform injection across the entire cross-sectional area of a combustor inlet, the current research sought to conceptualize, design, and test a bi-propellant RDE with a symmetric injector pattern, and elucidate detonation propagation. In this investigation, different injector patterns concepts were studied, and a symmetric, square, lattice pattern injector was designed and fitted to a square combustion chamber. Combustion tests were conducted with mass flowrates between 30-38 g/s, equivalence ratios between 1.0-1.6, and from back pressures of approximately 5 kPa. Experimental data revealed unidirectional detonation wave motion, reflected waves coexisting with the detonation wave under stable operation, non-uniform pressure near the combustor inlet, increased wave velocity compared to a previous hollow engine tested at Nagoya University, potentially improved reactant mixing in the chamber, and a 94° phase shift when decomposing the detonation wave motion into rectangular coordinates.

  • Operating Characteristics of Rotating Detonation Engine with Different Liquid Fuel for Next Sounding Rocket Space Flight

    Matsushita T., Sato T., Suzuki S., Matsuoka K., Itouyama N., Yasui M., Ide Y., Kasahara J., Kawasaki A., Nakata D., Eguchi H., Uchiumi M., Matsuo A., Funaki I.

    AIAA Science and Technology Forum and Exposition AIAA Scitech Forum 2026  2026

    　View Summary

    Liquid propellants are widely used in rocket engines, and investigating the operational characteristics of RDEs using liquid propellants is essential for their practical application. In this study, combustion experiments were conducted on a single-annular RDE using liquid propane and liquid nitrous oxide as propellants, and its operational characteristics were evaluated. As a result, successful operation in the detonation mode was achieved with an operating frequency of 15–16 kHz. However, a gradual decrease in the propane mass flow rate was observed during combustion. This behavior was attributed to the possible occurrence of vapor lock in the propane injector feed lines caused by heat generated during combustion. To examine this possibility, the injector feed line wall temperature was calculated using the heat conduction equation under the assumptions of a one-dimensional semi-infinite solid, a constant incoming heat flux, and single-phase liquid flow in the injector. The results showed that for an incoming heat flux of q=0.2 MW/m2, the wall temperature near the injector outlet exceeds the boiling temperature of propane, indicating the potential for bubble formation at the injector outlet.

  • Numerical Evaluation of the Thermal Response of HIMICO with a Cork-Sandwich TPS

    Kashiwakura K., Matsuo A., Shima E., Taguchi H., Takahashi H., Momose M.

    27th AIAA International Space Planes and Hypersonic Systems and Technologies Conference  2026

    　View Summary

    In this study, a three-dimensional conjugate heat transfer (CHT) analysis was conducted for the entire hypersonic experimental vehicle (HIMICO), including its internal thermal protection system (TPS), to evaluate the thermal response characteristics and thermal integrity of the vehicle under the wind tunnel test conditions at Ramjet Engine Test Facility in JAXA. The results indicated that, after 30 s of exposure to the high-temperature flow, the temperatures of certain regions of the Ti-6Al-4V structural components and the Cork insulation material exceeded their allowable operating limits, suggesting the potential for degradation of material strength and deterioration of thermal insulation performance. Comparison with wind tunnel test data showed good agreement in the surface temperature distributions at both the nose cone tip and the wing region, thereby demonstrating the validity of the present analysis approach. Furthermore, the results revealed that small geometric features, such as bolt holes, can significantly affect localized temperature rises and should therefore be considered in detailed thermal design evaluations.

  • Design Analyses and Demonstration Tests of High-Mach Integrated Control Experiment Aircraft (HIMICO)

    Taguchi H., Sato T., Tezuka A., Fujio C., Tsue M., Tsuchiya T., Nakaya S., Takizawa K., Matsuo A., Hirotani T., Takahashi H., Hongoh M., Koga M., Isono T.

    27th AIAA International Space Planes and Hypersonic Systems and Technologies Conference  2026

    　View Summary

    Design analyses were conducted on the hypersonic integrated control experimental aircraft (HIMICO) that flies at Mach 5. Aerodynamic performance of the aircraft was obtained by hypersonic wind tunnel experiments and CFD analyses. Structural feasibility in a high-temperature flight environment was confirmed by fluid-structure coupling simulation and structural analyses. The control law of hypersonic air intake was confirmed by hypersonic wind tunnel test. The control law of hydrogen ram combustor was confirmed by direct connect combustion experiments. The aerodynamic force measurements and flow field measurements for propulsion wind tunnel tests with Mach 5 flight simulating condition were prepared. Mechanical environment tests of onboard equipment were conducted simulating the onboard environment of sounding rocket.

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Papers, etc., Registered in KOARA 【 Display / hide 】

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Reviews, Commentaries, etc. 【 Display / hide 】

  • Simulation Technology Supporting the Development of Supersonic Combustor

    松尾 亜紀子

    Journal of the Combustion Society of Japan (The Combustion Society of Japan)  67 ( 220 ) 71 - 76 2025.05

    Article, review, commentary, editorial, etc. (scientific journal), Single Work, Lead author, Corresponding author

  • 特集　航空宇宙分野御コンピューターシミュレーション

    松尾　亜紀子　他

    計算工学 28 ( 3 )  2023.07

    Article, review, commentary, editorial, etc. (scientific journal), Corresponding author

  • 爆発現象等に関する安全工学の研究に従事する理工学部機械工学科女性教授ープラントにおける爆発現象ー

    松尾　亜紀子

    高圧ガス (高圧ガス保安協会)  57 ( 1 ) 23 - 27 2020.01

    Article, review, commentary, editorial, etc. (other), Single Work,  ISSN  0452-2311

  • 極超音速飛しょう体におけるサボ分離挙動に関する数値解析

    笠原弘貴, 松尾亜紀子

    防衛技術ジャーナル (一般財団法人　防衛技術協会)  2019年9月号 ( 462 ) 46 - 52 2019.09

    Rapid communication, short report, research note, etc. (scientific journal), Joint Work

  • 化学プラント爆発事象再現へ向けた燃焼過程の解析技術

    松尾亜紀子

    安全工学 (安全工学会)  57 ( 6 ) 465 - 470 2018.12

    Article, review, commentary, editorial, etc. (scientific journal), Single Work,  ISSN  0570-4480

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Presentations 【 Display / hide 】

  • Experimental Investigation of a Coupled Multi-Cylindrical Rotating Detonation Engine with Slit

    Nakama, A., Inamori, S., Itouyama, N., Matsuoka, K., Yasui, M., Kasahara, J., Matsuo, A., and Funaki, I.

    [International presentation]  10th EDITION OF THE 3AF INTERNATIONAL CONFERENCE ON SPACE PROPULSION (BARI, ITALY) , 

    2026.05
    , 

    Oral presentation (general)

  • Numerical Analysis of Unsteady Behavior in a Detonation-Assisted Fuel Injection System Using a Cylindrical RDC

    Miyashita, M., Matsuo, A., Shima, E., Itouyama, N., Kawasaki, A., Matsuoka, K., and Kasahara, J.

    [International presentation]  The 14ｔh International Workshop On Detonation For Propulsion (IWDP2026) (Yokohama, Japan) , 

    2026.05
    , 

    Oral presentation (general)

  • Numerical Investigation of a Reflective Shuttling Detonation Combustor as a Parallel Fuel Injector for Supersonic Airflow

    Sato, H., Matsuo, A., and Shima, E.

    [International presentation]  The 14ｔh International Workshop On Detonation For Propulsion (IWDP2026) (Yokohama, Japan) , 

    2026.05
    , 

    Poster presentation

  • Numerical Investigation of the Interaction Between Blast Wave and Structures in Large-Scale Explosions

    Nakajima, K., and Matsuo, A.

    [International presentation]  16th International Symposium on Hazards, Prevention and Mitigation of Industrial Explosions (ISHPMIE2026) (Kaohsiung, Taiwan) , 

    2026.04
    , 

    Oral presentation (general)

  • Symmetric, Square, Lattice Pattern Injector Design and Experimental Flow Characterization within a Detonation Engine

    Joseph V., Kasahara J., Matsuoka K., Itouyama N., Yasui M., Ide Y., Matsuo A., Funaki I., Higashino K.

    [International presentation]  AIAA Scitech Forum 2026 (Orland, Florida, U.S.A.) , 

    2026.01
    , 

    Oral presentation (general)

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Research Projects of Competitive Funds, etc. 【 Display / hide 】

  • 多分散系微粉体がもたらす爆発被害：シミュレーションが解き明かす炭塵燃焼と安全評価

    2018.04
    -
    2021.03

    MEXT,JSPS, Grant-in-Aid for Scientific Research, Grant-in-Aid for Scientific Research (B), Principal investigator

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Intellectual Property Rights, etc. 【 Display / hide 】

  • パルスデトネーションエンジン用多孔微細管燃料酸化剤供給プレート

    Date applied： 2000-258181  2000.07 

    Date announced： 2002-39012  2002.02 

    Patent, Joint

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Awards 【 Display / hide 】

  • 2023年度日本燃焼学会論文賞

    川﨑央, 稲川 智也, 笠原次郎, 後藤 啓介, 松岡健, 松尾亜紀子, 船木一幸, 2023.11, 日本燃焼学会, Critical condition of inner cylinder radius for sustaining rotating detonation waves in rotating detonation engine thruster

    Type of Award： Award from Japanese society, conference, symposium, etc.

  • Fluids Science Research Award

    2023.11, 一般財団法人 機器研究会

    Type of Award： International academic award (Japan or overseas)

  • Pressure Gain Combustion Best Paper Award 2022

    K. Goto, K. Matsuoka, K. Matsuyama, A. Kawasaki, H. Watanabe, N. Itouyama, K. Ishihara, V. Buyakofu, T. Noda, J. Kasahara (Nagoya Univ.), A. Matsuo（Keio Univ.）, I. Funaki (JAXA), D. Nakata, M. Uchiumi (Muroran Inst. Tech.), H. Habu, S. Takeuchi, S. Arakawa, J. Masuda, K. Maehara, T. Nakao, K. Yamada (JAXA), 2023.01, AIAA, Flight Demonstration of Detonation Engine System Using Sounding Rocket S-520-31: Performance of Rotating Detonation Engine

    Type of Award： Award from international society, conference, symposium, etc.,  Country： United States

    　View Description

    深宇宙探査用デトネーションエンジンの宇宙飛行実証論文に対しAIAAが2022 AIAA Pressure Gain Combustion Best Paper Awardを授与。2021年7月27日に名古屋大学、宇宙航空研究開発機構、慶應義塾大学、室蘭工業大学との共同研究として観測ロケットS-520-31号機の第２段を用いてデトネーションエンジンの宇宙飛行実証を実施した。その結果を論文として公開し、その研究論文に対し、AIAAからBest Paper Awardを授与された。この賞は圧力増大燃研究（デトネーションエンジン研究）で2022年に米国航空宇宙学会で発表された口頭発表論文の内、優れた１件に授与される。

  • 2021年『美しい炎』の写真展最優秀作品賞

    松尾亜紀子 他, 2021.11, 一般社団法人　日本燃焼学会, World First! Detonation Engine Space Demonstration

    Type of Award： Award from Japanese society, conference, symposium, etc.

  • 2020年『美しい炎』の写真展最優秀作品賞

    松尾亜紀子 他, 2020.12, 一般社団法人　日本燃焼学会, Detonation Engine to Space

    Type of Award： Award from Japanese society, conference, symposium, etc.

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Courses Taught 【 Display / hide 】

  • AERO-SPACE ENGINEERING

    2026

  • INDEPENDENT STUDY ON SCIENCE FOR OPEN AND ENVIRONMENTAL SYSTEMS

    2026

  • INTRODUCTION TO FLUID MECHANICS

    2026

  • GRADUATE RESEARCH ON ENGINEERING AND DESIGN 1

    2026

  • GRADUATE RESEARCH ON SCIENCE FOR OPEN AND ENVIRONMENTAL SYSTEMS 2

    2026

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Courses Previously Taught 【 Display / hide 】

  • 応用計算力学特論第１

    Keio University

    2014.04
    -
    2015.03
    , 

    Spring Semester, Lecture

  • 理工学基礎実験

    Keio University

    2014.04
    -
    2015.03
    , 

    Spring Semester, Laboratory work/practical work/exercise, Lecturer outside of Keio

  • 宇宙推進工学

    Keio University

    2014.04
    -
    2015.03
    , 

    Spring Semester, Lecture

  • 応用計算力学特論第２

    Keio University

    2014.04
    -
    2015.03
    , 

    Autumn Semester, Lecture

  • 機械工学創造演習

    Keio University

    2014.04
    -
    2015.03
    , 

    Autumn Semester, Seminar, Lecturer outside of Keio

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Social Activities 【 Display / hide 】

  • 世界と日本の宇宙開発について知り、 宇宙工学の一端を学ぼう

    株式会社ナガセ，東進ハイスクール, 東進ハイスクール　大学学部研究会 講義ダイジェスト2026年度版, 

    , 
    2026.07

    　View Summary

    東進ハイスクールで受講している高校生を対象に、大学での研究内容を紹介している冊子

  • 「宇宙開発の最新動向について」〜宇宙は「遠い世界」から「私たちの身近なビジネス」へ〜

    日本航空協会, 日本航空協会 第314回講演会 (航空会館 7階大ホール)

    , 
    2026.06

  • 数学科、情報科学科卒業生が語る「変革を担う、女性であること」

    津田塾大学, 津田塾大学 理科創設80周年記念シンポジウム (津田塾大学)

    , 
    2024.10

  • デトネーションエンジン開発状況とシミュレーション事例の紹介

    アドバンスソフト株式会社, 第3回 アドバンス・シミュレーション・セミナー 2024 (オンラインセミナー (Zoom）)

    , 
    2024.06

  • 津田塾スピリットを体現する卒業生たち。

    都市出版株式会社, 東京人 July 2024 No.481, 

    , 
    2024.06

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Media Coverage 【 Display / hide 】

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Memberships in Academic Societies 【 Display / hide 】

  • International Association for Hydrogen Safety, 

    2015.07
    -
    Present

  • International Shock Wave Institute, 

    2013
    -
    Present

  • 日本計算工学会, 

    2002.12
    -
    Present

  • 日本火災学会, 

    2002.11
    -
    2021

  • 日本原子力学会, 

    2002.11
    -
    2007.03

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Committee Experiences 【 Display / hide 】

  • 2026.07
    -
    2028.06

    科学技術会議 委員, 神奈川県

  • 2026.06
    -
    2028.05

    産業構造審議会 製造産業分科会 宇宙産業小委員会 委員, 経済産業省

  • 2026.04
    -
    2030.03

    評議員, 三菱ガス化学記念財団

  • 2026.04
    -
    2028.03

    ⼤学外部評価委員, 学校法人芝浦工業大学

  • 2026.04
    -
    2028.03

    複合原子力科学研究所運営委員会委員、共同利用運営委員会委員, 京都大学

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