In the present work, numerical results of ice accretion prediction on the UH-1H helicopter rotor blade with a NACA 0012 airfoil are reported. During the winter of 1982-83, the NASA Lewis Research Center and the US Army conducted a helicopter icing flight test (HIFT) program using a UH-1H aircraft at the Canadian National Research Council spray rig at Uplands Airport, Ottawa, Canada. From several hover icing flight conditions conducted in the HIFT program, a test case is selected to be evaluated with numerical analysis. The computation is performed at an airspeed of 4.6 m/s, ambient temperature of -19.0°C, liquid water content of 0.7 g/m3 and an exposure time of 3 minutes. In order to reproduce the experimental aerodynamic conditions the three-dimensional flow field is numerically computed. Both a two-dimensional and three-dimensional approach is followed to predict the ice shape. In the first phase, two different ice accretion codes are used: the NASA Glenn LEWICE with a Reynolds-averaged Navier Stokes (RANS) solver and the MULTI-ICE code, developed by CIRA. The approach of these solvers to carry out the simulation is similar. The ice accretion simulation is performed by calculating the two-dimensional aerodynamic conditions, the impingement region and the final iced shape for several sections along the span of the rotor, extrapolating the operating conditions from the three-dimensional flow field with a step-by-step technique until the total exposure time is reached. In the second phase, a direct three-dimensional ice accretion computation is carried out using a code developed by CIRA. Comparisons with experimental data are shown.
Ice Accretion Prediction on Helicopter Rotor Blade in Hover Flight
Sae Technical Papers
2007 SAE Aircraft and Engine Icing International Conference ; 2007
2007-09-24
Conference paper
English
Ice Accretion Prediction on Helicopter Rotor Blade in Hover Flight
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