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Acceleration of astronomical shock waves: Low temperature electrons and nonthermal high energy surf-riding acceleration

Autor: Hoshino, Masahiro

Publikováno v: 平成14年度宇宙放射線シンポジウム:次期X線天文衛星NeXTは何を目指すか = Cosmic Radiation Symposium 2002: New Science to be Explored by the X-ray Astronomy Mission NeXT. :61-64

資料番号: AA0045914008

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::be55d0e3314726b956591b46fe332eb7
http://id.nii.ac.jp/1696/00038154/

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Wind tunnel test of the RLV basic structure: Understanding of the effect of the slenderness ratio

Autor: Tsuboi, Nobuyuki, Fujimoto, Keiichiro, Fujii, Kozo, Irikado, Tomoko, Sato, Kiyoshi

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. :47-50

資料番号: AA0045913013

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::07caf5dd13006805072e71e19824c0c6
http://id.nii.ac.jp/1696/00014694/

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ロケットエンジンノズル内部流れの数値計算

Autor: Shimizu, Taro, Miyajima, Hiroshi, Nakahashi, Kazuhiro

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2002論文集 = Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2002. 57:166-171

The purpose of this study is the numerical investigation of the origin of the side-load generated in the LE-7A rocket engine nozzle during the start-up and shut-down transient operation. So far, the origin of the side-load causing the maximum load of

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::17e223688d86af5a171258537c748e94
http://id.nii.ac.jp/1696/00038245/

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航空機舵角変化に対する空力応答の数値シミュレーション

Autor: Murayama, Mitsuhiro, Togashi, Fumiya, Nakahashi, Kazuhiro, Matsushima, Kisa, Kato, Takuma

In this paper, numerical simulations of aerodynamic response to changes of the deflection angle of a longitudinal control surface of NAL experimental supersonic airplanes are discussed. To treat the change of the deflection angle of the control surfa

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::ce26aba7d0e892676cfe46d4c2ff2b7f
http://id.nii.ac.jp/1696/00038267/

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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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Comparison of CFD results for the flow around NEXST-1: Detailed study on CFD results at 3rd SST-WS

Autor: Takaki, Ryoji, Yamamoto, Kazuomi, Yoshida, Kenji

This paper presents comparison of EFD/CFD results submitted to the 3rd SST-WorkShop held in December 2001. Comparison among CFD results shows mostly good agreement. However, it shows big discrepancy in C(sub D) estimation. Comparison between CFD and

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::9e4626a01ad05c457cb6f4df66bb522d
http://id.nii.ac.jp/1696/00038230/

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Study on the supersonic aerodynamic characteristics of the entire body at the reentry of the vehicle with an membrane aeroshell

Autor: Yamada, Kazuhiko, Suzuki, Kojiro, Hongo, Motoyuki

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. :99-102

資料番号: AA0045913026

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::8df5e28420d0974febc0689d48bd53c2
http://id.nii.ac.jp/1696/00014707/

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Experimental study on the improvement of L/D ratio by a variable wing end method

Autor: Hiraki, Koju, Sato, Kiyoshi

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. :79-82

資料番号: AA0045913021

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::05a931717e5a72fc80d235c71732e24b
http://id.nii.ac.jp/1696/00014702/

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弱い音波による層流剥離の数値計算

Autor: Ishii, Katsuya, Suzuki, Satoshi, Adachi, Shizuko

Publikováno v: 航空宇宙技術研究所特別資料: 境界層遷移の解明と制御研究会講演論文集第29回・第30回 = Special Publication of National Aerospace Laboratory: Proceedings of the 29th and 30th NAL Workshops on Investigation and Control of Boundary-Layer Transition. 56:7-10

The effect of acoustic excitation on the laminar separated flows over an NACA0012 airfoil with the angle of attack 12 deg, at the Reynolds numbers Re = 1 x 10(exp 5), 5 x 10(exp 4) and at the Mach number M = 0.1 investigated numerically. The amplitud

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::a4278109a07d8729612f883c9bb1dfa7
http://id.nii.ac.jp/1696/00038188/

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Subscale wind tunnels and supplemental studies of scramjet engine tests

Autor: Mitani, Toru, Hiraiwa, Tetsuo, Kanda, Takeshi, Shimura, Takashi, Tomioka, Sadatake, Kobayashi, Kan, Izumikawa, Muneo, Sakuranaka, Noboru, Watanabe, Shuichi, Tarukawa, Yuichi

Publikováno v: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory. 1458

航空宇宙技術研究所・角田推進研究所ではラムジェットエンジン試験設備(RJTF)を完成し、水素を燃料とするスクラムジェットエンジンやメタン燃料ラムジェット(HYPR用)エンジンを試験し�

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::6660d684ec05c2d5d38fd091f50cf5ab
http://id.nii.ac.jp/1696/00042859/

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