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- ICHIKAWA Akio
- 名古屋大学大学院航空工学専攻
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- ANDO Shigenori
- 名古屋大学工学部航空学教室
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- NAKAZIMA Kunio
- トヨタ自動車工業株式会社
Bibliographic Information
- Other Title
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- 亜音速揚力面の数値計算誤差に関する覚え書
- アオンソク ヨウリョクメン ノ スウチ ケイサン ゴサ ニ カンスル オボエガ
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Abstract
A numerical investigation is performed on the three discrete models (δ type, step type, and linear type) for lifting airfoils. Types of downwash investigated are that of flat plate (w=1) as well as those of wavy plates (w=cos mθ). Collocation method is used to determine the strength of vortex distributions.<BR>The following results are obtaind: a) A number E is appropriately defined as a measure of lift distribution errors. b) For accuracy, the δ type is best which is followed by the linear type and then by the step type. c) The control point locations should be at the 75% point for the δ type, 85-95% point for the step type, and 60-90% point for the linear type. d) The locations of error-estimation should be at the 25% point for the δ type, 50% point for the Step type, and 0% (=100%) point for the linear type. e) The error E versus number of panels N are plotted on log-log graphs. through which we can predict the number of panels necessary for a speciled accuracy. Also linearity of this log-log graphs serves as an indication how the method is superior. f) For error concentration to the both edge panels, the δ type is most predominant over the other types.
Journal
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- Aeronautical and Space Sciences Japan
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Aeronautical and Space Sciences Japan 25 (287), 575-581, 1977
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
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Details 詳細情報について
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- CRID
- 1390001204507410048
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- NII Article ID
- 130003958219
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- NII Book ID
- AN00189072
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- ISSN
- 24241369
- 00214663
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- NDL BIB ID
- 1919686
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- Text Lang
- ja
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- Data Source
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- JaLC
- NDL
- Crossref
- CiNii Articles
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- Abstract License Flag
- Disallowed