Výsledky vyhledávání - "Nishio, Masatomi"

Study of flow structures around vehicle traveling at supersonic/hypersonic speeds

Autor: Nakamura, Hiroaki, Manabe, Keiji, Sezaki, Shinji, Nishio, Masatomi

Publikováno v: 宇宙航行の力学シンポジウム平成15年度 = Symposium on Flight Mechanics and Astrodynamics 2003. :47-50

Flow structures around a hypersonic re-entry Mars Environmental Survey (MESUR) capsule traveling at supersonic/hypersonic speeds are investigated utilizing a new computational method based on the finite element method (FEM). In order to confirm the v

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::0857235215efc7e6b9c32d816941cceb
http://id.nii.ac.jp/1696/00014652/

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Study on flowfield around winged TSTO launch vehicle by visualization using the electrical discharge method

Autor: Sezaki, Shinji, Nakamura, Hiroaki, Nishio, Masatomi, Yamamoto, Yukimitsu

Publikováno v: 宇宙航行の力学シンポジウム平成15年度 = Symposium on Flight Mechanics and Astrodynamics 2003. :119-122

The visualization of flowfield around a winged TSTO (Two Stage To Orbit) launch vehicle model has been carried out using the electrical discharge method. In this report, boundary layers and three-dimensional (lateral and cross-sectional) shock shapes

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::384ccbecba9229c50e5d05c0dfe931d8
http://id.nii.ac.jp/1696/00014670/

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Study on flowfield around future TSTO launch vehicle

Autor: Sezaki, Shinji, Nakamura, Hiroaki, Nishio, Masatomi

Publikováno v: 宇宙航行の力学シンポジウム平成14年度 = Symposium on Flight Mechanics and Astrodynamics 2002. :59-62

In this study, the flowfield around future TSTO Launch Vehicle was investigated by utilizing an electric discharge method. The experiments were carried out under the condition that the angles of attack of the model are -10, 0, and 10 deg. Shock shape

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::fdb53728a12322a580c988447a642623
http://id.nii.ac.jp/1696/00014697/

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Investigation of flowfield around hypersonic space plane

Autor: Nakamura, Hiroaki, Manabe, Keiji, Sezaki, Shinji, Nishio, Masatomi

Publikováno v: 宇宙航行の力学シンポジウム平成14年度 = Symposium on Flight Mechanics and Astrodynamics 2002. :63-66

The flowfield analysis around a model of space plane traveling at Mach 10 has been carried out utilizing the Electric Discharge Method and the Finite Element Method (FEM) scheme. The Electric Discharge Method can visualize almost all important hypers

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::9eb5fe750a16d2b40b8bd3364fd57848
http://id.nii.ac.jp/1696/00014698/

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Numerical simulation of flowfield around space plane traveling at Mach 10

Autor: Manabe, Keiji, Sezaki, Shinji, Nishio, Masatomi

Publikováno v: 航空宇宙技術研究所特別資料: 航空宇宙数値シミュレーション技術シンポジウム2001論文集 = Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2001. 53:257-261

The numerical simulation around a space plane traveling at the speed of Mach 10 was carried out based on FEM (Finite Element Method). In this FEM formulation, stress (pressure) term is partially integrated in an element by applying the weighted resid

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::a3bba89e87bf936946b8bb60aa4047c0
http://id.nii.ac.jp/1696/00038074/

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Shock Wave Analysis by Non-conservative FEM Formulation

Autor: Manabe, Keiji, Nishio, Masatomi

Publikováno v: 宇宙航空研究開発機構特別資料: 第41回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2009論文集 = JAXA Special Publication: Proceedings fo 41st Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2009.

平成21年6月18-19日. 宇宙航空研究開発機構調布航空宇宙センター
18 June-19 June, 2009, Japan Aerospace Exploration Agency
The hypersonic -flow including shock wave problems are usually analyzed by solving compressible

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::76c17402fe1c4a2efc39f2600621c76c
http://id.nii.ac.jp/1696/00004910/

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Stabilization time of the flow field around spacecraft in an experiment using a shock tunnel

Autor: Nishio, Masatomi, Manabe, Keiji, Sezaki, Shinji, Nakamura, Hiroaki

Publikováno v: 宇宙航行の力学シンポジウム平成15年度 = Symposium on Flight Mechanics and Astrodynamics 2003. :29-30

資料番号: AA0047120008

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::e3f0159d8a813b2413339d54e46ba3b0
http://id.nii.ac.jp/1696/00014647/

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Akademický článek

Visualization of Slow Structure Around a Hypersonic Re-entry Capsule Using the Electrical Discharge Method.

Autor: Nishio, Masatomi, Sezaki, Shinji, Nakamura, Hiroaki

Publikováno v: Journal of Visualization; 2004, Vol. 7 Issue 2, p151-158, 8p

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Akademický článek

Measurements of Capsule Wake Stabilization Times in a Hypersonic Gun Tunnel.

Autor: Nishio, Masatomi¹ m.nishio@fume.fukuyama-u.ac.jp, Sezaki, Shinji¹, Nakamura, Hiroaki¹

Publikováno v: AIAA Journal. Jan2004, Vol. 42 Issue 1, p56-60. 5p. 12 Diagrams, 5 Graphs.

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Akademický článek

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