An investigation of the transonic performance characteristics of several noise-suppressor configurations has been conducted in the Langley 16-foot transonic tunnel. The models were tested statically and over a Mach number range from 0.70 to 1.05 at an angle of attack of 0 deg. The primary jet total-pressure ratio was varied from 1.0 (jet off) to about 4.5. The effect of secondary air flow on the performance of two of the configurations was investigated. A hydrogen peroxide turbojet-engine simulator was used to supply the hot-jet exhaust. An 8-lobe afterbody with centerbody, short shroud, and secondary air had the highest thrust-minus-drag coefficients of the six noise-suppressor configurations tested. The 12-tube and 12-lobe afterbodies had the lowest internal losses. The presence of an ejector shroud partially shields the external pressure distribution of the 8-lobe after-body from the influence of the primary jet. A ring-airfoil shroud increased the static thrust of the annular nozzle but generally decreased the thrust minus drag at transonic Mach numbers.


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    Title :

    Transonic Performance Characteristics of Several Jet Noise Suppressors


    Contributors:

    Publication date :

    1960


    Size :

    50 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Transonic Performance Characteristics of Several Jet Noise Suppressors

    Schmeer, James W. / Salters, Leland B., Jr. / Cassetti, Marlowe D. | NTRS | 1960


    Transonic performance characteristics of several jet noise suppressors

    Schmeer, J.W. / Salters, Jr., L.B. / Cassetti, M.D. | Engineering Index Backfile | 1960


    Transonic performance characteristics of several jet noise suppressors

    Schmeer, James W. / Salters, Leland B. / Cassetti, Marlowe D. | TIBKAT | 1960



    Transonic drag of several jet-noise suppressors

    North, W.J. | Engineering Index Backfile | 1958