A 1/9-scale model of the AMSA was tested in the Propulsion Wind Tunnel, Transonic (16T) and Propulsion Wind Tunnel, Supersonic (16S) of the Propulsion Wind Tunnel Facility (PWT). The test vehicle consisted of an airplane model and two pressure-instrumented inlet nacelles. Airplane model variations representing three-engine and four-engine configurations were tested with the two engine nacelles representing either two-thirds or one-half of the full airplane configuration. The three-engine configuration consisted of one pylon-mounted nacelle under the left wing and one tail-mounted nacelle above the fuselage on the airplane vertical centerline. The symmetrical four-engine configurations had either two adjacent nacelles suspended under the left wing or one forward nacelle under the left wing and one nacelle mounted aft on the left side of the fuselage near the tail. Data were obtained at free-stream Mach numbers from 0.60 to 2.30 to determine the performance characteristics of the inlets, and the effects of mutual interactions of inlets and airplane surfaces. The model attitude was varied throughout an angle-of-attack range of -4 to +11 deg and yaw angles of plus or minus 4 deg.


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    Titel :

    Wind Tunnel Investigation of a 1/9-Scale Boeing Company AMSA Airplane-Inlet Model at Transonic and Supersonic Mach Numbers


    Beteiligte:
    D. C. Baker (Autor:in)

    Erscheinungsdatum :

    1967


    Format / Umfang :

    61 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch