Noise and performance test results are presented for a full-scale advanced design rectangular array lobe jet suppressor nozzle (plain wall and corrugated). Flight design and installation considerations are also discussed. Noise data are presented in terms of peak PNLT (perceived noise level, tone corrected) suppression relative to the existing airplane and one-third octave-band spectra. Nozzle performance is presented in terms of velocity coefficient. Estimates of the hot thrust available during emergency (engine out) with the suppressor nozzle installed are compared with the current thrust levels produced by the round convergent nozzles. (Author)


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    Title :

    Jet Noise Suppressor Nozzle Development for Augmentor Wing Jet STOL Research Aircraft (C-8A Buffalo)


    Contributors:
    D. L. Harkonen (author) / C. C. Marks (author) / J. V. Okeefe (author)

    Publication date :

    1974


    Size :

    144 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Static Noise Tests on Augmentor Wing Jet STOL Research Aircraft (C8a Buffalo)

    C. C. Marrs / D. L. Harkonen / J. V. Okeefe | NTIS | 1974


    Static noise tests on augmentor wing jet STOL research aircraft (C8A Buffalo)

    Marrs, C. C. / Harkonen, D. L. / Okeefe, J. V. | NTRS | 1974