Three-dimensional SBLI control for transonic airfoils

Holger Babinsky, Hideaki Ogawa

Research output: Chapter in Book/Report/Conference proceedingConference contribution

7 Citations (Scopus)


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.

Original languageEnglish
Title of host publicationCollection of Technical Papers - 3rd AIAA Flow Control Conference
Number of pages8
Publication statusPublished - 2006
Externally publishedYes
Event3rd AIAA Flow Control Conference - San Francisco, CA, United States
Duration: Jun 5 2006Jun 8 2006

Publication series

NameCollection of Technical Papers - 3rd AIAA Flow Control Conference


Other3rd AIAA Flow Control Conference
Country/TerritoryUnited States
CitySan Francisco, CA

All Science Journal Classification (ASJC) codes

  • Engineering(all)


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