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風洞試験における二、三の問題について(遷音速での試験精度を阻害する要因)
https://jaxa.repo.nii.ac.jp/records/43544
https://jaxa.repo.nii.ac.jp/records/435447e613c2d-a8b5-44df-9b4b-ee225d7d1f2d
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
nalsp0016048.pdf (887.4 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 | 風洞試験における二、三の問題について(遷音速での試験精度を阻害する要因) | |||||||||
| 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 | Two Problems Reducing the Data Accuracy in Transonic Wind tunnel Testing | |||||||||
| 著者 |
河本, 巖
× 河本, 巖
× Kawamoto, Iwao
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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-16 巻 16, p. 305-312, 発行日 1991-12 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | Two problems concerning the data accuracy in transonic wind tunnel testing are described. One is the side wall boundary layer interference problem in the airfoil testing. In the transonic airfoil testing, it is believed that the side wall B.L. suction brings the improvement of the two-dimensionality of the airfoil surface flow. But it is not so simple. In NAL 2D high Reynolds number transonic wind tunnel, the measurements of side wall boundary layer thickness, Mach number distribution along center line and pressure distribution on NACA0012 airfoil were conducted with and without side wall boundary layer suction through a pair of rigimeshes. Following conclusions are derived in the present experimental studies. The B.L. suction system was not useful for the improvement of the airfoil surface flow, then theoretical side wall boundary layer correction such as Barnwell and Murthy methods should be employed to the data used solid side walls at the present time. Another problem presented here is transition Reynolds number of the experimental model. Using the AEDC standard cone, transition Reynolds numbers in several large transonic wind tunnels including NAL2m x 2mTWT are compared with flight data emphasizing the effects of back ground noise Cprms. Present comparative study shows that at low Mach number region Cprms does not promote the transition point forward and at high Mach number region the transition point is moved forward with large Cprms. | |||||||||
| 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: NALSP0016048 | |||||||||
| 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-16 | |||||||||
