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    Wind tunnel test results of a new leading edge flap design for highly swept wings, a vortex flap (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A leading edge flap design for highly swept wings, called a vortex flap, was tested on an arrow wing model in a low speed wind tunnel. A vortex flap differs from a conventional plain flap in that it has a leading edge tab which is counterdeflected from the main portion of the flap. This results in intentional separation at the flap leading edge, causing a vortex to form and lie on the flap. By trapping this vortex, the vortex flap can result in significantly improved wing flow characteristics relative to conventional flaps at moderate to high angles of attack, as demonstrated by the flow visualization results of this tests.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Supersonic Cruise Res. 1979, Pt. 1; p 131-147
    Format: application/pdf
    Location Call Number Expected Availability
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