Tests made to determine range of advance ratio and blade angle in which tunnel wall corrections as developed for wings might be used for rotors; lift and drag coefficient data were corrected by standard wing-type wall corrections using full span of rotor as vortex span and area of rotor disk as wing area; data compared to determine at which blade angles and advance ratios corrections gave satisfactory agreement.


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    Titel :

    Experimental investigation of effect of wind tunnel walls on aerodynamic performance of helicopter rotor


    Weitere Titelangaben:

    NASA -- Tech Note


    Beteiligte:
    Ganzer, V.M. (Autor:in) / Rae, Jr., W.H. (Autor:in)


    Erscheinungsdatum :

    1960


    Format / Umfang :

    35 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :



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