The Icing Research Tunnel is used extensively to test many classes of aircraft under atmospheric icing conditions. Because of the need to test models at higher Reynolds numbers, a new fan rotor was designed to increase test section wind speed. A preliminary study was made of the present fan rotor to suggest possible methods to increase tunnel wind speed. The results of that study are presented.


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    Titel :

    Calculated Performance of the NASA Lewis Icing Research Tunnel


    Beteiligte:
    L. A. Viterna (Autor:in)

    Erscheinungsdatum :

    1991


    Format / Umfang :

    23 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





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