1,720,972 research outputs found
Multi-physics simulation of in-flight ice shedding
Full text linkIn-flight ice accretion may possibly jeopardise the safety of fixed-and rotary-wing aircraft. Icing can possibly occur if supercooled water droplets in clouds impinge on the aircraft surfaces and freeze upon impact. A major issue related to ice accretion is the possibility of ice shedding from the main body and impacting other parts of the aircraft or being ingested by the engines. A multi-physics framework is presented to simulate ice accretion and shedding from wings and engine nacelles due to aerodynamic forces. The aerodynamics is computed using the open-source tool-kit SU2. Cloud droplet trajectories are computed using the arbitrary-precision Lagrangian in-house solver PoliDrop. Then, the in-house ice accretion tool-kit PoliMIce is used to determine the ice layer. A FEM structural analysis is performed on the accreted ice shape by means of the open-source code MoFEM. Internal stresses within the ice geometry due to aerodynamic forces are computed. The possibility of the occurrence of cracks in the ice layer is assessed and its propagation is determined numerically. Two-dimensional ice accretion simulations are performed to check the validity of the present approach and compare fairly well with available results
Implementation of [Gamma]-Re0 Transition Model within SU2: Model Validation and Verification
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Valutazione della risposta anticorpale IgG mediata verso Ag. Alimentari valutata mediante metodica ELISA
No full textValutazione della risposta anticorpale IgG mediata verso Ag. Alimentari valutata mediante metodica ELIS
A Three-Dimensional Level-Set Front Tracking Technique for Automatic Multi-Step Simulations of In-Flight Ice Accretion
No full textMulti-Fidelity Assessment of the Aerodynamic Performances of Unconventional Aircraft Tail Configurations
No full textWe adopt a multi-fidelity approach for investigating the aerodynamic performances of an unconventional “Advanced Rear End” component for the forthcoming generation of ultra-efficient aircraft. Namely, we numerically predict the aerodynamic coefficients of unconventional tail configurations using tools of different fidelity e.g., a mid-fidelity model based on the Reynolds-Averaged Navier-Stokes (RANS) approximation and a low-fidelity model based on the potential flow assumption. Numerical predictions are then compared, in order to assess their reliability with respect to the whole range of expected operating conditions and tail geometrical configurations. In future works, numerical results will be also compared against wind-tunnel experiments planned at the large wind tunnel in Politecnico di Milano
A Comprehensive Numerical Model for Numerical Simulation of Ice Accretion and Electro-Thermal Ice Protection System in Anti-icing and De-icing Mode, with an Ice Shedding Analysis
No full textNumerical Simulation of Rotorcraft In-Flight Icing and Shedding via a High-Fidelity Method
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