4-ft diam 2-blade rotor was tested in 300-mph 7×10 ft Langley tunnel to study effect of blade collective pitch angle, rotor angle of attack, flapping hinge offset, and tip speed ratio during stages of transformation between helicopter and autogiro configuration; results obtained.


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    Title :

    Wind-tunnel investigation of effect of angle of attack and flapping-hinge offset on periodic bending moments and flapping of small rotor


    Additional title:

    NASA -- Memo


    Contributors:


    Publication date :

    1959


    Size :

    44 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :


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