An inlet-coldpipe assembly was placed in a Mach 0.4 stream to ingest the tip vortex of a forward mounted wing. The strongest vortex was produced by a wing angle of attack of 11 degrees. The vortex displayed a tangential velocity of 57 percent of local stream velocity prior to entering the inlet, and a tangential velocity of 25 percent of local velocity at the simulated comotal-pressure profiles measured by standard compressor-face rakes were changed by the presence of the vortex only at the highest tested inlet mass-flow ratios. (Author)


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    Titel :

    Preliminary Investigation of Inlet Ingestion of a Wing Tip Vortex


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

    Erscheinungsdatum :

    1973


    Format / Umfang :

    42 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch