Computational Fluid Dynamics with Icing Effects

Paper #:
  • 932532

Published:
  • 1993-09-01
Citation:
Mouch, T. and Lan, C., "Computational Fluid Dynamics with Icing Effects," SAE Technical Paper 932532, 1993, https://doi.org/10.4271/932532.
Pages:
14
Abstract:
A quick, computationally inexpensive technique has been developed for the analysis of a full aircraft configuration with iced surfaces. Viscous effects for the flow field about an airfoil with an iced leading edge are accounted for in a thin-layer Navier-Stokes code (ARC2D). A panel code (PMARC) solves the flow field away from the body. The results of the airfoil analysis represent the near-field solutions and are used to modify the boundary conditions in the three-dimensional calculations with the panel code by matching the local circulation. This process is repeated until the total lift coefficient between successive iterations differs by less than a specified value. Examples showing good comparison between the 3-D calculations and experimental data are provided.
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