The experimental low-speed aerodynamic characteristics of an axisymmetric mixed-compression supersonic inlet with variable cowl slot are described. The model consisted of the NASA P-inlet centerbody and redesigned cowl with variable cowl slot powered by the JT8D single-stage fan simulator and driven by an air turbine. The model was tested in the NASA Lewis Research Center 9- by 15-foot low-speed tunnel at Mach numbers of 0, 0.1, and 0.2 over a range of flows, cowl slot openings, centerbody positions, and angles of attack. The variable cowl slot was effective in minimizing lip separation at high velocity ratios, showed good steady-state and dynamic distortion characteristics, and had good angle-of-attack tolerance.


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    Title :

    Low-Speed Aerodynamic Test of an Axisymmetric Supersonic Inlet with Variable Cowl Slot


    Contributors:
    A. G. Powell (author) / H. R. Welge (author) / C. J. Trefny (author)

    Publication date :

    1985


    Size :

    6 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English