An empirical model to predict the effects of flight on the noise from a supersonic transport is developed. This model is based on an analysis of the exhaust jet noise from high subsonic flights of the F-15 ACTIVE Aircraft. Acoustic comparisons previously attainable only in a wind tunnel were accomplished through the control of both flight operations and exhaust nozzle exit diameter. Independent parametric variations of both flight and exhaust jet Mach numbers at given supersonic nozzle pressure ratios enabled excellent correlations to be made for both jet broadband shock noise and jet mixing noise at flight speeds up to Mach 0.8. Shock noise correlated with flight speed and emission angle through a Doppler factor exponent of about 2.6. Mixing noise at all downstream angles was found to correlate well with a jet relative velocity exponent of about 7.3, with deviations from this behavior only at supersonic eddy convection speeds and at very high flight Mach numbers. The acoustic database from the flight test is also provided.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Supersonic Jet Exhaust Noise at High Subsonic Flight Speed


    Contributors:
    T. D. Norum (author) / D. P. Garber (author) / R. A. Golub (author) / O. L. Santa Maria (author) / J. S. Orme (author)

    Publication date :

    2004


    Size :

    90 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Supersonic Jet Exhaust Noise at High Subsonic Flight Speed

    Norum, Thomas D. / Garber, Donald P. / Golub, Robert A. et al. | NTRS | 2004



    Effect of Simulated Forward Flight on Subsonic Jet Exhaust Noise

    A.B. Packman / K.W. Ngt / R. W. Paterson | AIAA | 1976



    Simulated High Speed Flight Effects On Supersonic Jet Noise

    Norum, T. D. / Brown, M. C. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 1993