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Second-Order Supersonic Small Disturbance Theory
https://jaxa.repo.nii.ac.jp/records/34373
https://jaxa.repo.nii.ac.jp/records/34373ca171f4e-f7a0-4578-aa0c-be77d769eb91
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
SA2400490.pdf (4.6 MB)
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| Item type | 紀要論文 / Departmental Bulletin Paper(1) | |||||||
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| 公開日 | 2015-03-26 | |||||||
| タイトル | ||||||||
| タイトル | Second-Order Supersonic Small Disturbance Theory | |||||||
| 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 |
KARASHIMA, Keiichi
× KARASHIMA, Keiichi
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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 1, p. 1-49, 発行日 1965-01 |
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| 抄録（英） | ||||||||
| 内容記述タイプ | Other | |||||||
| 内容記述 | A study of plane and axially symmetric supersonic flow is made for the approximate inviscid theory of such comparatively thick bodies that the linearized equation does not adequately predict an essential feature of flow. The second-order small disturbance equations are derived for plane and axially symmetric motions involving shock waves and the range of applicability is shown from order estimation of the error involved in the approximation. For very high supersonic Mach numbers it is shown that the present approach is reduced to the first-order hypersonic small disturbance theory proposed by Van Dyke and, there fore, a single small disturbance theory may predict the flow at all supersonic speeds above the trasonic. Several examples are numerically calculated for two-dimensional biconvex circular-arc airfoils, cones and a paraboloid-arc half-body of revolution with respect to their surface pressure distribution and initial shock wave curvature, etc., and compared with full solutions and other approximate solutions when available. Experimental measurement of surface pressure distribution and observation of shape of the shock wave are made for a paraboloid-arc half-body of revolution with fineness ratio of 6.693 and for Mach numbers of 2,3 and 8,and the results are compared with those of the present theory and others. It is concluded that the present theory agrees well with the method of characteristics and the experimental results also confirm the present approach. | |||||||
| 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: SA2400490000 | |||||||
