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The A06 test facility designed for combustor testing in altitude has been modified to be converted in an icing facility for probe testing. The objective was to be able to simulate ice crystals conditions at high altitude, high Mach number and low temperature. This facility has been upgraded in several steps extending the median size of the ice crystals produced and the ice water content range. The aero-thermal and icing capabilities have been assessed during commissioning tests. Finally, in order to prepare the calibration of the facility, some measurement techniques for cloud characterization have been selected or developed, especially for cloud uniformity measurement.

This paper deals with the development and the validation of a SLD capability in the DGA Aero-engine Testing icing altitude test facility S1 and with the results of the EXTICE 2D SLD icing tests campaign on a NACA 0012 airfoil. A new kind of SLD atomizer has been developed and characterized prior to being installed on the S1 sprays bars for freezing drizzle calibration tests. For 2D icing tests, a specific set-up has been designed and validated. Some results of the SLD atomizer characterization, calibration tests, 2D test methodology validation and EXTICE SLD 2D icing tests are presented.

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.