Maximum rotor lift capability is investigated using wind-tunnel test data of McHugh (modified 1/10-scale CH-47B rotor) and a full-scale UH-60A rotor. Rotor performance calculations with the comprehensive rotorcraft analysis CAMRAD II are compared with the wind-tunnel test data. The analysis of the McHugh rotor with the Reynolds-number-corrected airfoil table shows good correlation with the measurements for μ = 0.1 to 0.5 and is able to predict the maximum rotor lift reasonably well, especially at 0.2 μ 0.4 . The analysis is also able to predict the maximum lift of the full-scale UH-60A rotor within about 3.5% at μ = 0.24 and 0.3. Calculations with dynamic stall models, in general, show only a small influence on the rotor performance and are not necessary to predict maximum lift. Airfoils have an important role in defining the maximum lift capability of the rotor. The VR-12 airfoil, which has stall characteristics superior to the baseline V23010 airfoil, substantially improves the maximum lift capability of the McHugh rotor, showing the potential to improve the behavior of a rotor by improving the airfoil’s static stall characteristics.


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    Title :

    Prediction of Maximum Lift Capability of Helicopter Rotors


    Contributors:

    Published in:

    Journal of Aircraft ; 52 , 1 ; 257-265


    Publication date :

    2015-01-01




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





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