Accurate measurement of location where laminar boundary layer undergoes transition to turbulent one serves many purposes in basic aero-dynamic research and developmental testing. Individual gages must be staggered to prevent formation of turbulence at gages downstream. This arrangement precludes accurate measurements of laminar/turbulent transition regions along streamline. Complete understanding of performance, stability, and control of laminar-flow airplane requires knowledge of transition locations on wing surface, empennage surfaces, fuselage, and nacelles. Visual, acoustic, and electronic methods capable of providing this transition information.


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    Title :

    Continuous, Multielement, Hot-Film Transition Gage


    Contributors:
    Holmes, B. (author) / Mcpherson, J. (author) / Harris, F. (author) / Diamond, J. (author) / Johnson, N. (author) / Chapman, J. (author)

    Published in:

    Publication date :

    1986-05-01



    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :


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