Personnel at the NASA Langley Research Center (NASA-Langley) and the NASA Dryden Flight Research Facility (NASA-Dryden) recently completed a joint acoustic flight test program. Several types of aircraft with high nozzle pressure ratio engines were flown to satisfy a twofold objective. First, assessments were made of subsonic climb-to-cruise noise from flights conducted at varying altitudes in a Mach 0.30 to 0.90 range. Second, using data from flights conducted at constant altitude in a Mach 0.30 to 0.95 range, engineers obtained a high quality noise database. This database was desired to validate the Aircraft Noise Prediction Program and other system noise prediction codes. NASA-Dryden personnel analyzed the engine data from several aircraft that were flown in the test program to determine the exhaust characteristics. The analysis of the exhaust characteristics from the F-18 aircraft are reported. An overview of the flight test planning, instrumentation, test procedures, data analysis, engine modeling codes, and results are presented.


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    Title :

    Flight-determined engine exhaust characteristics of an F404 engine in an F-18 airplane


    Contributors:

    Conference:

    AIAA/SAE/ASME/ASEE Joint Propulsion Conference and Exhibit ; 1993 ; Monterey, CA, United States


    Publication date :

    1993-10-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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