A helicopter blade profile was tested in the DGA Aero-engine Testing's icing altitude test facility S1 in Saclay, France during the winter of 2013/2014. The airfoil was a helicopter main rotor OA312 blade profile made out of composite material and with a metallic erosion shield. Dry air and ice accretion tests have been performed in order to assess the iced airfoil's aerodynamic behaviour. Several icing conditions were tested up through Mach numbers around 0.6. This paper presents the test setup, the test model and some of the test results. The test results presented in this paper include the ice shapes generated as well as dry air and iced airfoil lift and drag curves (polars) which were obtained with the real ice shapes on the airfoil.


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    Title :

    2D Polar Assessment in Icing Wind Tunnel for iced Helicopter Blade Profiles


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    SAE 2015 International Conference on Icing of Aircraft, Engines, and Structures ; 2015



    Publication date :

    2015-06-15




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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