Wings, designed for leading edge thrust at supersonic speeds, were investigated in the Unitary Plan Wind Tunnel at Mach numbers of 1.60, 1.80, 2.00, 2.16, and 2.36. Experimental data were obtained on a uncambered wing which had three interchangeable leading edges that varied from sharp to blunt. The leading edge thrust concept was evaluated. Results from the investigation showed that leading edge flow separation characteristics of all wings tested agree well with theoretical predictions. The experimental data showed that significant changes in wing leading edge bluntness did not affect the zero lift drag of the uncambered wings.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Experimental investigation of leading-edge thrust at supersonic speeds


    Contributors:
    Wood, R. M. (author) / Miller, D. S. (author)

    Publication date :

    1983-09-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :