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2D Polar Assessment in Icing Wind Tunnel for iced Helicopter Blade Profiles
ISSN: 0148-7191, e-ISSN: 2688-3627
Published June 15, 2015 by SAE International in United States
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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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CitationMunzing, A., Hervy, F., and Catris, S., "2D Polar Assessment in Icing Wind Tunnel for iced Helicopter Blade Profiles," SAE Technical Paper 2015-01-2127, 2015, https://doi.org/10.4271/2015-01-2127.
- Hervy F. AIAA 2011-38-0086 New SLD Icing Capabilities at DGA Aero-engine Testing
- Jérôme E. , Hervy F. , Maguis S. 49th Applied Aerodynamics Symposium Lille, France 24 25 26 March 2014 Overview of Icing Test Capabilities at DGA Aero-engine Testing