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Aerodynamic Characterization of Linear Aerospike Nozzles in Off-Design Flight Conditions
https://jaxa.repo.nii.ac.jp/records/22521
https://jaxa.repo.nii.ac.jp/records/225216bc2e212-89b4-4849-88e2-9e040e6c77ec
Item type | 学術雑誌論文 / Journal Article(1) | |||||
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公開日 | 2015-05-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Aerodynamic Characterization of Linear Aerospike Nozzles in Off-Design Flight Conditions | |||||
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 | |||||
アクセス権 | ||||||
アクセス権 | metadata only access | |||||
アクセス権URI | http://purl.org/coar/access_right/c_14cb | |||||
著者 |
Takahashi, Hidemi
× Takahashi, Hidemi× Tomioka, Sadatake× Tomita, Takeo× Sakuranaka, Noboru |
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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) | ||||||
出版者(英) | ||||||
出版者 | American Institute of Aeronautics and Astronautics (AIAA) | |||||
書誌情報 |
en : Journal of Propulsion and Power 巻 31, 号 1, p. 204-218, 発行日 2015-01 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Spike surface flowfields and base wake behaviors of clustered linear aerospike nozzles under the presence of external flow were characterized using surface pressure measurements, flow visualizations using the background-oriented schlieren method, and theoretical modeling. The test model consisted of three clustered cell nozzle modules or a nonclustered two-dimensional nozzle with an exit Mach number of 3.5, followed by a straight section and a contoured spike. The model was exposed to an external flow of Mach 2.0 to simulate off-design transonic flight conditions. The measured surface pressure distributions indicated that the entire flowfield on the spike surface became more two-dimensional under the presence of external flow. Periodic compressions and expansions of the cell nozzle jet were eliminated, but the pressure continued to increase downstream. The results of the flow visualizations found that this was mainly governed by the external flow that controls the jet expansion by forming a slip surface. This mechanism also made the spike base pressure higher than environmental pressure. The physics-based model predicted the measured surface pressure distribution well and explained the mechanism behind the influence of external flow. The effects of the external flow showed improvements in thrust performance in off-design flight conditions. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0748-4658 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA10459896 | |||||
DOI | ||||||
識別子タイプ | DOI | |||||
関連識別子 | http://dx.doi.org/10.2514/1.B35342 | |||||
関連名称 | info:doi/10.2514/1.B35342 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: PA1510019000 |