A low-boom supersonic inlet was designed for use on a conceptual small supersonic aircraft that would cruise with an over-wing Mach number of 1.7. The inlet was designed to minimize external overpressures, and used a novel bypass duct to divert the highest shock losses around the engine. The Wind-US CFD code was used to predict the effects of capture ratio, struts, bypass design, and angles of attack on inlet performance. The inlet was tested in the 8-ft by 6-ft Supersonic Wind Tunnel at NASA Glenn Research Center. Test results showed that the inlet had excellent performance, with capture ratios near one, a peak core total pressure recovery of 96 percent, and a stable operating range much larger than that of an engine. Predictions generally compared very well with the experimental data, and were used to help interpret some of the experimental results.


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    Title :

    Computational Analysis of a Low-Boom Supersonic Inlet


    Contributors:

    Conference:

    29th Applied Aerodynamics Conference ; 2011 ; Honolulu, HI, United States


    Publication date :

    2011-11-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English






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