The oncoming of a new generation of subsonic transport aircraft (with supercritical wing and high by-pass ratio turbofans) led to an experimental study of wing nacelle jet pylon interference in transonic flow. To this end, a test set-up was developed at the ONERA S3Ch wind tunnel. The nacelle models represent a turbofan by means of two compressed air jets. The scale is 1/18.5. The nacelles are fixed on a thrust balance measuring afterbody thrust and discharge coefficients. The wing is located between the sidewalls of the test section. Pressures are measured through 456 holes located on 8 airfoils. Drag coefficient of the wing is obtained by wake survey. The following parameters can vary (1) wing/nacelle position; (2) upstream Mach number (from 0.3 to 0.8); (3) jet pressure ratio; (4) with/without pylon and (5) type of nacelle. Wing nacelle interference can be studied by means of total thrust drag analysis as a functon of the various parameters. The test set-up is described and examples of results are presented.


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    Titel :

    Experimental Study of the Interaction Between the Wing of a Subsonic Aircraft and a Nacelle of a High by-Pass Ratio Engine


    Beteiligte:
    P. Levart (Autor:in)

    Erscheinungsdatum :

    1981


    Format / Umfang :

    28 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





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