書誌事項
- タイトル別名
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- Lift Characteristic of Blunt Trailing Edge Aerofoils Formed by Cutting the Rear of NACA0012.
- NACA0012 ノ コウエン オ セツダンシタ ニブイ コウエン ノ ツバサ
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The lift characteristic of blunt trailing edge NACA0012 aerofoil is investigated with a Göttingen type low speed wind tunnel and the results are compared with discrete vortices calculation method. The balance test is performed at Re=3.5×105 and the pressure distributions over the wing surface are measured at Re=4.7×105. The followings are known: (1) the lift slope of a blunt trailing edge aerofoil is greater than the one of the sharp trailing edge NACA0012, (2) the pressure distributions upstream to the trailing edge cutting point are little changed by the cutting, and (3) the lift slope of a blunt trailing edge aerofoil is higher than the sharp trailing edge aerofoil for the same thickness ratio.
収録刊行物
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- 日本航空宇宙学会誌
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日本航空宇宙学会誌 45 (516), 62-66, 1997
一般社団法人 日本航空宇宙学会
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詳細情報 詳細情報について
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- CRID
- 1390001204477184512
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- NII論文ID
- 10002861318
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- NII書誌ID
- AN00189072
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- ISSN
- 24241369
- 00214663
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- NDL書誌ID
- 4117320
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- 本文言語コード
- ja
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- データソース種別
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- JaLC
- NDL
- Crossref
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- 抄録ライセンスフラグ
- 使用不可