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OZAWA Hiroshi  小澤 啓伺

ORCIDConnect your ORCID iD *help
Researcher Number 00712738
Other IDs
Affiliation (based on the past Project Information) *help 2020 – 2021: 東京都立大学, システムデザイン研究科, 准教授
2013 – 2014: 首都大学東京, システムデザイン研究科, 助教
Review Section/Research Field
Principal Investigator
Basic Section 24010:Aerospace engineering-related / Aerospace engineering
Keywords
Principal Investigator
熱流束 / 衝撃波干渉 / 感温塗料計測法 / 感温塗料 / 境界層遷移 / 極超音速流 / 極超音速 / 空力加熱率 / 高速応答型感温塗料計測法 / hypersonic / TSP / shock wave
  • Research Projects

    (2 results)
  • Research Products

    (3 results)
  •  Research on Shock-Wave/Boundary-Layer Interaction and Hypersonic Boundary-Layer Transition due to a wall-mounted protuberance using TSPPrincipal Investigator

    • Principal Investigator
      小澤 啓伺
    • Project Period (FY)
      2020 – 2021
    • Research Category
      Grant-in-Aid for Scientific Research (B)
    • Review Section
      Basic Section 24010:Aerospace engineering-related
    • Research Institution
      Tokyo Metropolitan University
  •  Development of Ultra-fast response Temperature-Sensitive-Paint capable of temperature measuring in 1ms test durationPrincipal Investigator

    • Principal Investigator
      OZAWA Hiroshi
    • Project Period (FY)
      2013 – 2014
    • Research Category
      Grant-in-Aid for Research Activity Start-up
    • Research Field
      Aerospace engineering
    • Research Institution
      Tokyo Metropolitan University

All Other

All Presentation

  • [Presentation] 衝撃波管内壁を利用した高速応答型感温塗料計測法の実験的研究

    • Author(s)
      小澤 啓伺
    • Organizer
      第58回宇宙科学技術連合講演会
    • Place of Presentation
      長崎
    • Year and Date
      2014-11-12 – 2014-11-14
    • Data Source
      KAKENHI-PROJECT-25889047
  • [Presentation] 高速応答型TSPを用いた衝撃波管壁面上の衝撃波速度と空力加熱率の計測

    • Author(s)
      小澤 啓伺
    • Organizer
      日本流体力学会年会2014
    • Place of Presentation
      仙台
    • Year and Date
      2014-09-15 – 2014-09-17
    • Data Source
      KAKENHI-PROJECT-25889047
  • [Presentation] Visualization of Unsteady Boundary-Layer Transition on Shock-Tube Wall using Highly Sensitive Fast-response TSP

    • Author(s)
      Ozawa Hiroshi
    • Organizer
      20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference (Hypersonics 2015), 発表予定
    • Place of Presentation
      Glasgow, Scotland
    • Year and Date
      2015-07-06 – 2015-07-09
    • Data Source
      KAKENHI-PROJECT-25889047

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