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  1. コンテンツタイプ
  2. 紀要論文 (Departmental Bulletin Paper)
  1. 機関資料(JAXA, former ISAS, NAL, NASDA)
  2. 旧機関資料 (JAXA, former-ISAS, NAL, NASDA)
  3. 宇宙科学研究所: ISAS Report等を含む (former ISAS (The Institute of Space and Astronautical Science): Including ISAS Report etc.)
  4. ISAS report/Institute of Space and Aeronautical Science,University of Tokyo

Experimental Studies in a Low Density Gun Tunnel Stream

https://jaxa.repo.nii.ac.jp/records/34375
https://jaxa.repo.nii.ac.jp/records/34375
80dfe1e6-5c82-452b-8011-a5b4ea53e675
名前 / ファイル ライセンス アクション
SA2400496.pdf SA2400496.pdf (1.2 MB)
Item type 紀要論文 / Departmental Bulletin Paper(1)
公開日 2015-03-26
タイトル
タイトル Experimental Studies in a Low Density Gun Tunnel Stream
言語 en
言語
言語 eng
資源タイプ
資源タイプ識別子 http://purl.org/coar/resource_type/c_6501
資源タイプ departmental bulletin paper
著者 OGUCHI, Hakuro

× OGUCHI, Hakuro

en OGUCHI, Hakuro

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HONMA, Hiroki

× HONMA, Hiroki

en HONMA, Hiroki

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FUNABIKI, Katsushi

× FUNABIKI, Katsushi

en FUNABIKI, Katsushi

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出版者
出版者 東京大学宇宙航空研究所
出版者(英)
出版者 Institute of Space and Aeronautical Science,University of Tokyo
書誌情報 en : ISAS report/Institute of Space and Aeronautical Science,University of Tokyo

巻 30, 号 3, p. 83-100, 発行日 1965-01
抄録(英)
内容記述タイプ Other
内容記述 First the flow survey is made for the low-density hypersonic flow, which is achieved by a low-density operation of the gun tunnel (or free piston compression). In particular the measurements of flow velocity and, hence, of stagnation temperature are worked out by means of an explosion-wire technique and the flow survey done by traversing a free molecule calorimeter in the test flow region. With these diagnostics the characteristic feature of the test flow is investigated. It is found that, by a low-density operation of the present gun tunnel, the test flow of Mach number 10 and Reynolds number 650 (per cm) is achieved, which is applicable to experimental studies on low-density hypersonic flow problems. Secondly an experimental study is made concerning the shock-layer structure ahead of a sphere in a low-density hypersonic flow, achieved by the present gun tunnel. The scanning-electron-beam densitometer is developed to obtain a density distribution along a scanning path of the beam during one shot of the gun tunnel. By means of this device the density distribution across the shock layer is measured for a sphere of 12.4mm in radius, in which case the Reynolds Re_∞ is about 800. The present data exhibit a qualitative agreement with Lcvinsky-Yoshihara profile which was computed for argon flow of Mach number M=10 and Re_∞=10^3 and 10^2.
ISSN
収録物識別子タイプ ISSN
収録物識別子 0372-1418
書誌レコードID
収録物識別子タイプ NCID
収録物識別子 AA00675986
資料番号
内容記述タイプ Other
内容記述 資料番号: SA2400496000
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