An investigation has been conducted in the static test facility of the Langley 16-Foot Transonic Tunnel to determine the effects of rounding and rotating the port corner of a nonaxisymmetric thrust reversing port. High pressure air was used to simulate jet exhaust at nozzle pressure ratios up to 6.0. The investigation indicates that using a rounded corner in the reverser port passage increases the discharge coefficient significantly compared to that of a sharp cornered thrust reversing port. Incorporating a rotating cylinder into the rounded corner reverser port passage provides no additional increase at cylinder revolutions per minute up to 10,000. (Revolutions per minute of 390,000 were necessary to achieve a surface velocity equal to the duct velocity.) Highest levels of discharge coefficient are obtained by providing a large, round, cylindrical surface in the port upstream wall. Locating the reverser port in a constant area duct results in higher discharge coefficients than locating the port in a convergent duct.


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    Titel :

    Investigation at Static Conditions of Nonaxisymmetric Nozzle Thrust Reverser Port Geometry Including Effects of Rounding and Rotating the Port Corner


    Beteiligte:
    D. G. Arbiter (Autor:in)

    Erscheinungsdatum :

    1985


    Format / Umfang :

    56 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch