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Free-flight measurement technique in the free-piston high-enthalpy shock tunnel
https://jaxa.repo.nii.ac.jp/records/22409
https://jaxa.repo.nii.ac.jp/records/22409982f051a-045b-43a2-82cc-bba4d6b5d975
名前 / ファイル | ライセンス | アクション |
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PA1410044.pdf (3.0 MB)
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Item type | 学術雑誌論文 / Journal Article(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Free-flight measurement technique in the free-piston high-enthalpy shock tunnel | |||||
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 | journal article | |||||
著者 |
丹野, 英幸
× 丹野, 英幸× 小室, 智幸× 佐藤, 和雄× 藤田, 和央× Laurence, S. J.× Tanno, Hideyuki× Komuro, Tomoyuki× Sato, kazuo× Fujita, Kazuhisa× Laurence, S. J. |
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著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
ドイツ航空宇宙センター | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
German Aerospace Center | ||||||
出版者(英) | ||||||
出版者 | American Institute of Physics (AIP) | |||||
書誌情報 |
en : Review of Scientific Instruments 巻 85, 号 4, 発行日 2014-04 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | A novel multi-component force-measurement technique has been developed and implemented at the impulse facility JAXA-HIEST, in which the test model is completely unrestrained during the test and thus experiences free-flight conditions for a period on the order of milliseconds. Advantages over conventional free-flight techniques include the complete absence of aerodynamic interference from a model support system and less variation in model position and attitude during the test itself. A miniature on-board data recorder, which was a key technology for this technique, was also developed in order to acquire and store the measured data. The technique was demonstrated in a HIEST wind-tunnel test campaign in which three-component aerodynamic force measurement was performed on a blunted cone of length 316 mm, total mass 19.75 kg, and moment of inertia 0.152 kgm2. During the test campaign, axial force, normal forces, and pitching moment coefficients were obtained at angles of attack from 14° to 32° under two conditions: H0 = 4 MJ/kg, P0 = 14 MPa; and H0 = 16 MJ/kg, P0 = 16 MPa. For the first, low-enthalpy condition, the test flow was considered a perfect gas; measurements were thus directly compared with those obtained in a conventional blow-down wind tunnel (JAXA-HWT2) to evaluate the accuracy of the technique. The second test condition was a high-enthalpy condition in which 85% of the oxygen molecules were expected to be dissociated; high-temperature real-gas effects were therefore evaluated by comparison with results obtained in perfect-gas conditions. The precision of the present measurements was evaluated through an uncertainty analysis, which showed the aerodynamic coefficients in the HIEST low enthalpy test agreeing well with those of JAXA-HWT2. The pitching-moment coefficient, however, showed significant differences between low-and high-enthalpy tests. These differences are thought to result from high-temperature real-gas effects. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0034-6748 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA00817730 | |||||
DOI | ||||||
関連タイプ | isIdenticalTo | |||||
識別子タイプ | DOI | |||||
関連識別子 | http://dx.doi.org/10.1063/1.4870920 | |||||
関連名称 | info:doi/10.1063/1.4870920 | |||||
権利 | ||||||
権利情報 | (C)2014 AIP Publishing LLC | |||||
著者版フラグ | ||||||
出版タイプ | VoR | |||||
出版タイプResource | http://purl.org/coar/version/c_970fb48d4fbd8a85 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: PA1410044000 |