Airfoil Ice-Accretion Aerodynamics Simulation
Michael B. Bragg and Andy P. Broeren
University of Illinois, Urbana, Illinois, 61801
H. Addy and M. Potapczuk
NASA Glenn Research Center, Cleveland, Ohio 44135
D. Guffond and E. Montreuil
ONERA, Châtillon, France F-92322
ABSTRACT
NASA Glenn Research Center, ONERA and the University of Illinois are conducting
a major research program whose goal is to improve our understanding of the
aerodynamic scaling of ice accretions on airfoils. The program when it is
completed will result in validated scaled simulation methods that produce the
essential aerodynamic features of the full-scale iced-airfoil. This research
will provide some of the first, high-fidelity, full-scale, iced-airfoil
aerodynamic data. An initial study classified ice accretions based on their
aerodynamics into four types: roughness, streamwise ice, horn ice, and
spanwise-ridge ice. Subscale testing using a NACA 23012 airfoil was performed
in the NASA IRT and University of Illinois wind tunnel to better understand the
aerodynamics of these ice types and to test various levels of ice simulation
fidelity. These studies are briefly reviewed here and have been presented in
more detail in other papers. Based on these results, full-scale testing at the
ONERA F1 tunnel using cast ice shapes obtained from molds taken in the IRT will
provide full-scale iced airfoil data from full-scale ice accretions. Using
these data as a baseline, the final step is to validate the simulation methods
in scale in the Illinois wind tunnel. Computational ice accretion methods
including LEWICE and ONICE have been used to guide the experiments and are
briefly described and results shown. When full-scale and simulation aerodynamic
results are available, these data will be used to further develop computational
tools. Thus the purpose of the paper is to present an overview of the program
and key results to date.