| Item type |
テクニカルレポート / Technical Report(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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|
タイトル |
3次元ナビエ・ストークス方程式による遷音速流の数値計算 |
| 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 |
Numerical Simulation of Transonic Flow Fields by Solving the Three-Dimensional Navier-Stokes Equations |
| 著者 |
藤井, 孝蔵
吉田, 正廣
大林, 茂
Fujii, Kozo
Yoshida, Masahiro
Obayashi, Shigeru
|
| 著者所属 |
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|
航空宇宙技術研究所 |
| 著者所属 |
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|
航空宇宙技術研究所 |
| 著者所属 |
|
|
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東京大学工学部 |
| 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-5
巻 5,
p. 159-166,
発行日 1985-11
|
| 抄録（英） |
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|
内容記述タイプ |
Other |
|
内容記述 |
The LU-ADI factored scheme has been successfully applied to solving the three-dimensional compressible "thin-layer" Navier-Stokes equations. The computations were carried out for the slightly supersonic flow over a hemisphere cylinder at high incidence and for the transonic flow over a swept wing. To simulate these complicated flow fields, fine grid distributions up to about 200,000 points were used on a new Japanese supercomputer. The total cpu time for each case was less than two hours. The result for the flow over a hemisphere cylinder at high incidence revealed the existence of the shock wave and the detailed structure of the vertical flow field on the leeward side. The improved version of the LU-ADI scheme was then developed and used for the simulation of the viscous transonic flow fields over the main wing of a practical transportation aircraft. Excellent agreement was obtained between the calculated pressure distribution over the surface and that of the experiment. The three-dimensional complicated separation phenomenon was also revealed for the case of relatively high angle of attack. These results indicate the capability of the present code to simulate three-dimensional complicated flow fields. The application of the present code to more practical flow fields such as transonic flows over a wing-body combination of transportation aircraft is also very promising. Even simulation over the whole aircraft geometry may soon be possible. |
| ISSN |
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|
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 |
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収録物識別子タイプ |
NCID |
|
収録物識別子 |
AN10097345 |
| 資料番号 |
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|
内容記述タイプ |
Other |
|
内容記述 |
資料番号: NALSP0005021 |
| レポート番号 |
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|
内容記述タイプ |
Other |
|
内容記述 |
レポート番号: NAL SP-5 |
nalsp0005021.pdf (664.5 kB)
