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有限要素法による多翼素翼型まわりの粘性非圧縮性流れの解析
https://jaxa.repo.nii.ac.jp/records/43257
https://jaxa.repo.nii.ac.jp/records/432576ebb7d1b-d62f-40f8-af7b-27ec1775a7be
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
nalsp0008004.pdf (714.5 kB)
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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 | 有限要素法による多翼素翼型まわりの粘性非圧縮性流れの解析 | |||||||||
| 言語 | ||||||||||
| 言語 | jpn | |||||||||
| 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 | |||||||||
| その他のタイトル（英） | ||||||||||
| その他のタイトル | Finite Element Analysis of Incompressible Viscous Flow around Multi-Element Aerofoils | |||||||||
| 著者 |
重見, 仁
× 重見, 仁
× Shigemi, Masashi
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| 著者所属 | ||||||||||
| 航空宇宙技術研究所 | ||||||||||
| 著者所属（英） | ||||||||||
| en | ||||||||||
| National Aerospace Laboratory | ||||||||||
| 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特別資料 en : Special Publication of National Aerospace Laboratory SP-8 巻 8, p. 29-36, 発行日 1987-11 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | The Navier-Stokes equation was solved by the finite element method to simulate the laminar flow around aerofoils. The concept of the penalty function method was introduced in the finite element method to simplify the implication of the incompressibility constraint. The streamline upwind/Petrov-Galerkin (SU/PG) method was also incorporated to avoid the numerical oscillation in the velocity field, which is known to appear when a simple finite element formulation is applied to flow problems in high Reynolds number region. Three examples were chosen to test the usability of the formulation developed. These are a flow around a symmetric aerofoil with zero angle of attack, a flow around an aerofoil which is known to show the laminar leading edge separation when the Reynolds number is fairly low, and a flow around an aerofoil with flap. All flows obtained showed separation. The separated region of all examples experienced unsteady periodic schedding of vortices except the one on the symmetric aerofoil with low Reynolds number, therefore the time marching follows of phenomena became necessary The theta-method was used to integrate equations with respect to time, with theta between 0.5 and 0.55. The calculated result shows reasonably good agreement with the measured result which accompanies the laminar separation. Even if the aerofoil is multi-elemented, there are no particular difficulties in application of this formulation in comparison with the case when the aerofoil is single-elemented. | |||||||||
| ISSN | ||||||||||
| 収録物識別子タイプ | ISSN | |||||||||
| 収録物識別子 | 0289-260X | |||||||||
| 書誌レコードID | ||||||||||
| 収録物識別子タイプ | NCID | |||||||||
| 収録物識別子 | AN10097345 | |||||||||
| 資料番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | 資料番号: NALSP0008004 | |||||||||
| 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 SP-8 | |||||||||
