Oscillating Iced Airfoil Pressure Measurement and Computation

A team from the US rotorcraft industry, NASA, and academia was established to further advance the development of icing analysis tools for rotorcraft. Validation data for the tools were obtained from a twodimensional oscillating airfoil test at the NASA Glenn Research Center Icing Research Tunnel in May 2010. A pressure instrumented SC-2210 airfoil section with an alternate leading-edge piece to simulate accreted ice was evaluated under steady and unsteady pitch conditions, including dynamic stall, to capture performance degradation for CFD code validation. In addition, measurements were taken under icing conditions which posed challenges as pressure taps were blocked by accreting ice. This paper provides an in-depth look at the results of the experimental surface pressures and loads for the clean airfoil, the simulated ice airfoil, and the iced airfoil. In addition, the experimental data are compared with analytical predictions obtained using two different solvers, OVERFLOW and GENCAS.