| One particular type of surface roughness that has become a critical area of research for aircraft designers is ice accretion. In this study, two problems that are encountered when modeling flow past aircraft icing are addressed: the geometric modeling of the ice shape and adequate resolution of the flow field to capture the relevant flow physics. As a partial solution to modeling of the ice shape, a specialized method based on Fourier analysis has been developed. This allows the algorithm to use actual ice shapes, obtained from experiments, in the flow calculations. As a solution to the second problem, the flow solver focuses a majority of the resources on the leading edge region where ice accretes, instead of having to solve the flow field around the entire wing. This allows a fine-grid region to be placed in areas of interest, which can capture flow phenomena that a coarse grid may miss. To verify the validity of the solutions, several test cases were run and compared to previous work, including flow past an isolated roughness element and a NACA 0012 airfoil in a rapid pitch-up maneuver. (Abstract shortened by UMI.)... |
