Titlebook: Handbook of Numerical Simulation of In-Flight Icing; Wagdi George Habashi Reference work 2024 Springer Nature Switzerland AG 2024 In-Fligh

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BOAST

Numerical Simulation of In-Flight Icing by a Multi-step Level-Set Method. This interaction is achieved by loosely coupling the flow and particles’ solvers to the ice accretion code in the simulation procedure. A quasi-steady approximation is made leveraging the different time scales at play: the total exposure time is subdivided into many smaller instants, after which t

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Numerical Simulation of In-Flight Icing by Coupled Immersed Boundary and Level-Set Methods models used by the industry. It allows the simulation of very complex ice forms with all difficult topographies, namely coalescing interfaces or severely separating ones. The Level- Set method allows a straightforward multi-step simulation. The solid boundary is treated in different methods, implic

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Numerical Simulation of In-Flight Icing Under Uncertain Conditionse epistemic and the aleatoric uncertainty inherent in the reality we aim at describing make the simulation process at least questionable, if not just poorly credible. For this reason, the numerical modeling of in-flight ice accretion cannot escape the utmost need for quantifying the uncertainty asso

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GRIN

Numerical Simulation of Convective Heat Transfer for In-Flight Icingent transition is essential in determining the final ice shape. The chapter presents the prediction of ice shapes via an improved treatment of the integral boundary layer. The onset of the laminar-turbulent regime is evaluated using an intermittency function to represent the transition region rather

HUMID

Numerical Simulation of In-Flight Iced Surface Roughness, such as shear stress and heat transfer, to predict ice shape formation over rough surfaces. The equivalent sandgrain roughness approach is the model commonly used in icing codes for the prediction of skin friction and heat fluxes over iced surfaces. Additional turbulent Prandtl number corrections

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Numerical Simulation of Iced Swept Wing Aerodynamics with RANS, DES, and IDDESto assess the ability of two Hybrid RANS-LES methods (DES and IDDES) to predict the aerodynamic performance parameters for a range of angles of attack where the flow is semi-detached. To support this objective, comparisons are made with aerodynamic results on a 65% scaled Common Research Model (CRM6

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