Three-dimensional SBLI control for transonic airfoils

Holger Babinsky, Hideaki Ogawa

研究成果: Chapter in Book/Report/Conference proceedingConference contribution

7 被引用数 (Scopus)

抄録

The application of shock control to transonic airfoils and wings has been demonstrated widely to have the potential to reduce wave drag. Most of the suggested control devices are two-dimensional, that is they are of uniform geometry in spanwise direction. Examples of such techniques include contour bumps and passive control. Recently it has been observed that a spanwise array of discrete three-dimensional controls can have similar benefits but also offer advantages in terms of installation complexity and drag. This paper describes research carried out in Cambridge into various three-dimensional devices, such as slots, grooves and bumps. In all cases the control device is applied to the interaction of a normal shock wave (M=1.3) with a turbulent boundary layer. Theoretical considerations are proposed to determine how such fundamental experiments can provide estimates of control performance on a transonic wing. The potential of each class of three-dimensional device for wave drag reduction on airfoils is discussed and surface bumps in particular are identified as offering potential drag savings for typical transonic wing applications under cruise conditions.

本文言語英語
ホスト出版物のタイトルCollection of Technical Papers - 3rd AIAA Flow Control Conference
ページ1751-1758
ページ数8
出版ステータス出版済み - 2006
外部発表はい
イベント3rd AIAA Flow Control Conference - San Francisco, CA, 米国
継続期間: 6 5 20066 8 2006

出版物シリーズ

名前Collection of Technical Papers - 3rd AIAA Flow Control Conference
3

その他

その他3rd AIAA Flow Control Conference
国/地域米国
CitySan Francisco, CA
Period6/5/066/8/06

All Science Journal Classification (ASJC) codes

  • 工学(全般)

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