A well-defined reference set of data for CFD and comprehensive code validation for a scaled helicopter main rotor with boundary layer transition in forward flight is presented (Fig. 1). The boundary layer transition was measured using differential infrared thermography (DIT) on the top (suction) side of the three-bladed NASA/Army “PSP rotor”, in the NASA Langley 14- by 22-Foot Subsonic Tunnel at an advance ratio of 0.3 (115kt).


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    Title :

    Boundary layer transition measured by DIT on the PSP rotor in forward flight


    Contributors:
    A. Gardner (author) / A. Weiss (author) / J. T. Heineck (author) / A. D. Overmeyer (author) / H. R. Spooner (author) / R. K. Jain (author) / C. C. Wolf (author) / M. Raffel (author)

    Publication date :

    2020


    Size :

    5 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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