A static test program was conducted to investigate aerodynamic and acoustic performance of a sonic inlet used as a noise suppressor. A translating centerbody type inlet with radial vanes was tested ahead of a J85-GE-13 turbojet engine. The inlet when fully choked, maintained high recovery with low distortions while dramatically reducing noise emanating from the compressor. Recoveries of 98.1% at simulated takeoff and 95% at approach were attained with associated sound attenuation of 40 db and 38 db respectively. Inlet lip shape was found to have significant effects on noise attenuation at these static conditions.


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    Title :

    Sonic inlet noise attenuation and performance with a J-85 turbojet engine as a noise source


    Contributors:

    Conference:

    Aerospace Sci. Meeting ; 1974 ; Washington, DC, United States


    Publication date :

    1974-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English