Numerical Investigation of Aerodynamic and Noise Characteristics of an Iced Multi-element Airfoil

Ice accretion on the aircraft components, such as wings and fuselage, can occur when the aircraft encounters a cloud zone with high humidity and low temperature. In particular, when icing grows on the wings of an aircraft, safety problems such as a decrease in aerodynamic performance and flight stability occur due to changes in external shape. In this study, a study on the aerodynamic and noise characteristics of an iced multi-element airfoil was conducted. The aerodynamic analysis was performed using the Lattice-Boltzmann method, and the permeable Ffowcs Williams-Hawking method predicted the noise based on the aerodynamic analysis results. First, aerodynamic analysis was performed at an angle of attack of 5.5 degrees for a multi-element airfoil without icing to validate the flow occurring in the slat element. Afterward, the flow was analyzed at the angle of attack of 8 degrees, which is the take off, landing angle, and 17 degrees, the angle near the stall, for the iced multi-element airfoil. Complex flow phenomena such as separation and recirculation zones caused by ice accretion on the leading edge were investigated, and the directivity of noise and primary source of noise generated from the iced multi-element airfoil were studied.