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Solutions for Compressible Separated Boundary Layers Including Supersonic Interaction
https://jaxa.repo.nii.ac.jp/records/44757
https://jaxa.repo.nii.ac.jp/records/447576e4f2b4d-5672-4abe-be06-756a17f8afd7
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr0503t.pdf (1.3 MB)
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| Item type | テクニカルレポート / Technical Report(1) | |||||||||
|---|---|---|---|---|---|---|---|---|---|---|
| 公開日 | 2015-03-26 | |||||||||
| タイトル | ||||||||||
| タイトル | Solutions for Compressible Separated Boundary Layers Including Supersonic Interaction | |||||||||
| 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_18gh | |||||||||
| 資源タイプ | technical report | |||||||||
| 著者 |
河合, 伸担
× 河合, 伸担
× KAWAI, Nobuhiro
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| 著者所属 | ||||||||||
| 航空宇宙技術研究所空気力学第二部 | ||||||||||
| 著者所属（英） | ||||||||||
| en | ||||||||||
| Second Aerodynamics Division, National Aerospace Laboratory(NAL) | ||||||||||
| 出版者 | ||||||||||
| 出版者 | 航空宇宙技術研究所 | |||||||||
| 出版者（英） | ||||||||||
| 出版者 | National Aerospace Laboratory(NAL) | |||||||||
| 書誌情報 |
航空宇宙技術研究所報告 en : Technical Report of National Aerospace Laboratory TR-503T 巻 503T, p. 19, 発行日 1977-06 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | This report first presents finite difference solutions for compressible laminar boundary-layer equations for flows with separation and reattachment. In order to avoid separation singularity, an inverse technique is used in which the displacement thickness is prescribed and the pressure is derived from the resulting solution. To eliminate unknown pressure from the whole formulation, a vorticity transfer equation and a modified stream function are introduced. To save computation time and storage, a forward marching procedure is adopted, for which streamwise convection terms must be neglected if the flow is reversed. Solutions are obtained by applying the Crank-Nicolson scheme and imposing certain conditions for convergence. A numerical method is next presented for calculation of interaction between outer supersonic flow and laminar boundary-layer flow including separation and reattachement. An interaction equation is obtained by equating the pressure gradient deduced from the supersonic linear theory and that from the momentum equation evaluated at the wall. The interaction equation is modified by adding an artificial-time term to it, and is solved by applying the alternating direction implicit scheme and using the foregoing inverse technique. Results are shown for boundary-layer flow with reverse flow regions over smooth compression ramps. | |||||||||
| ISSN | ||||||||||
| 収録物識別子タイプ | ISSN | |||||||||
| 収録物識別子 | 0389-4010 | |||||||||
| 資料番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | 資料番号: NALTR0503T000 | |||||||||
| レポート番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | レポート番号: NAL TR-503T | |||||||||
