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Flow field measurements of leading-edge separation vortex formed on a delta wing with vortex flaps

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Abstract

Wind tunnel tests are carried out using a 70 delta wing model with leading-edge vortex flaps. The structure of the leading-edge separation vortex over the leading-edge vortex flap is measured by use of a 5 holes pitot probe, surface pressure measurement technique and oil flow visualization technique. Separation vortices formed on a plain delta wing, on a vortex flap and inboard the vortex flap hinge line are clearly visualized. Results indicate that the flow around the vortex flaps is classified into several different cross flow patterns. The streamwise flap deflection angle is defined to discuss the vortex flap performance. The optimum lift to drag ratio is attained when the amount of the wing angle of attack is not far different from that of the streamwise flap deflection angle, as long as the vortex flap is deflected modestly.

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References

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Authors and Affiliations

  1. Department of Aeronautics and Astronautics, The University of Tokyo, Hongo, 113-8656, Tokyo, Japan

    Rinoie K.

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  1. Rinoie K.
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Additional information

Kenichi Rinoie: He received his M. eng. degree in Aeronautics in 1984 from The University of Tokyo. He recived Dr. Eng. degree in Aeronautics in 1988 from The University of Tokyo. He worked in Department of Aeronautics, The University of Tokyo as a research associate, in National Aerospace Laboratory as a senior researcher and in College of Aeronautics, Cranfield University as a visiting research fellow. He has been working in Department of Aeronautics and Astronautics, The University of Tokyo as an associate professor since 1993. His research interest covers aircraft design, separated flow aerodynamics and pilot human factors. He is a member of Royal Aeronautical Society (MRAeS, CEng).

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Rinoie, K. Flow field measurements of leading-edge separation vortex formed on a delta wing with vortex flaps. J Vis 4, 169–178 (2001). https://doi.org/10.1007/BF03182570

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  • DOI: https://doi.org/10.1007/BF03182570

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