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CFD is becoming an inevitable modern engineering tool in the vehicle aerodynamics. A LES based CFD approach is proposed for analysis for flows with complex geometrical configurations to which detailed experiments, high grid-density LES or DNS cannot be applicable. How CFD results should be evaluated for cases in which the related experiments are not available. The procedure proposed consists of four stages, i.e., inspections of solutions with coarse and fine meshes, reconfirmation of energy spectrum, references to the similar experiments, explanations of results obtained. The procedures are applied to the underbody flows with a semi-complex underbody configuration.

Ice accretion is a phenomenon in which supercooled water droplets impinge and accrete on a body. In the present study, we focus on a jet engine because it is well known that ice accretion on blades and vanes leads to performance degradation and has caused severe accidents. Although various anti-icing and deicing systems have been developed, such accidents still occur. Therefore, it is important to clarify the phenomenon of ice accretion in a jet engine. However, flight tests for ice accretion are very expensive, and in the wind tunnel it is difficult to reproduce every climate condition where ice accretion occurs. Therefore, it is expected that computational fluid dynamics (CFD), which can estimate ice accretion in various climate conditions, will be a useful way to predict the ice accretion phenomenon. The characteristic phenomena of supercooled large droplets (SLD) are splash and bounce.