A two-dimensional inlet and a turbojet engine were investigated in a Mach 0.4 stream so as to ingest the tip vortex of a forward mounted wing. Results show that ingestion of a wing tip vortex by a turbojet engine can cause a large reduction in engine stall margin. The loss in stall compressor pressure ratio was primarily dependent on vortex location and rotational direction and not on total-pressure variations across the compressor face. (Author)


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    Titel :

    Effect of Inlet Ingestion of a Wing Tip Vortex on Turbojet Stall Margin


    Beteiligte:
    G. A. Mitchell (Autor:in)

    Erscheinungsdatum :

    1974


    Format / Umfang :

    57 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch