A passive means of tailoring helicopter rotor blades to improve performance and reduce loads was evaluated. The parameters investigated were blade torsional stiffness, blade section camber, and distance between blade structural elastic axis and blade tip aerodynamic center. This offset was accomplished by sweeping the tip. The investigation was conducted at advance ratios of 0.20, 0.30, and 0.40. Data are presented without analysis; however, cross referencing of performance data and harmonic loads data may be useful to the analyst for validating aeroelastic theories and design methodologies as well as for evaluating passive aeroelastic tailoring or rotor blade parameters.


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    Title :

    Loads and Performance Data from a Wind-Tunnel Test of Model Articulated Helicopter Rotors with 2 Different Blade Torsional Stiffnesses


    Contributors:
    W. T. Yeager (author) / W. R. Mantay (author)

    Publication date :

    1983


    Size :

    322 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English