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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    Title :

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


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1960


    Size :

    35 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :



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