Velocity field for an airfoil with co-flow jet flow control

Adam Wells, Clark Conley, Bruce F. Carroll, Craig Paxton, Ge Cheng Zha

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

Abstract

The wind tunnel tests reported in this paper demonstrate the ability of the co-flow jet airfoil to dramatically increase lift, stall margin, and drag reduction. Detailed velocity field measurements are reported for a baseline NACA0025 airfoil and two variants of the baseline which implement the co-flow jet. The first variant has an injection slot size of 0.65% of chord while the second has an injection slot size twice that size.

Original languageEnglish (US)
Title of host publicationCollection of Technical Papers - 44th AIAA Aerospace Sciences Meeting
Pages10123-10131
Number of pages9
StatePublished - Dec 1 2006
Event44th AIAA Aerospace Sciences Meeting 2006 - Reno, NV, United States
Duration: Jan 9 2006Jan 12 2006

Publication series

NameCollection of Technical Papers - 44th AIAA Aerospace Sciences Meeting
Volume14

Other

Other44th AIAA Aerospace Sciences Meeting 2006
CountryUnited States
CityReno, NV
Period1/9/061/12/06

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ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Wells, A., Conley, C., Carroll, B. F., Paxton, C., & Zha, G. C. (2006). Velocity field for an airfoil with co-flow jet flow control. In Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting (pp. 10123-10131). (Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting; Vol. 14).