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Anti-Icing System Simulation and Ice Acceration on Wing in Cold & Humidity Weather

Rabiei Beheshti, Amin | 2012

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 44442 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Darbandi, Massoud
  7. Abstract:
  8. The attention to ice accretion subject and its implementation have recently become very serious in our country due to a substantial need to a further understanding of this phenomenon and improving the design and construction of anti-ice systems for the airplanes in-hand. The subject of this study is the numerical simulation of ice accretion at the surface of airplanes, which is a technical approach in aerospace engineering. In other words, this study simulates the details of ice growth at different sections of an airplane wing considering wide ranges of different affecting parameters and conditions. To achieve this, we numerically solve the governing equations for two-phase flow of air and super cooled droplets in theEulerianframe. We solve the Navier-Stokes equations to solve the air flow while the flow of droplets is separately treated using another form of the Navier-Stokes equations and assuming a permeable wall; in which the droplets can influence through that. We calculate the collection efficiency coefficient as one important parameter first. Having this parameter along the droplet velocities and the way they impinge the wing surface, the ice growth simulation becomes possible. We use the classical Messinger thermodynamic model to simulate the details of ice accretion. Our general intention is to simulate the ice growth for both 2D wing sections and 3D wings in this study. We also analyze the required power for an anti-ice system. It provides the necessary heat to avoid any ice growth at the wing surface in different ambient conditions. In the ice growth simulation part, we successfully merge two separate commercial softwares, i.e., the flow solver and the super cooled droplet solver, to obtain the current results. This coupling not only reduces the time for current simulation time but also provides more accurate solutions at some special ambient circumstances. We also develop a Fortran coed to calculate the minimum required heat, which suppresses any ice growth at the wing surface. The current results are compared with some other experimental data and numerical solutions. The comparison shows that the current study provides reliable and accurate solution in ice accretion simulation.
  9. Keywords:
  10. Aircraft ; Two Phase Flow ; Numerical Simulation ; Anti-Ice System ; Collection Efficiency Coefficient

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