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.
Computational fluid dynamics with icing effects
Rechnerische Dynamik von flüssigen Körpern in Bezug auf Vereisung im Luftfahrtbereich
SAE Technical Papers ; 1-12
1993
12 Seiten, 18 Bilder, 23 Quellen
Conference paper
English
Luftfahrttechnik , technische Entwicklung , Eisbildung , Tragflügel , Flugzeugrumpf , Flugzeugzelle , Fluid , Hydrodynamik , Rechenmodell , Prozessoptimierung , Navier-Stokes-Gleichung , Strömungsfeld , Grenzschicht , dreidimensionale Strömung , Vergleich (System) , experimentelle Untersuchung , Versuchsergebnis
Computational Fluid Dynamics with Icing Effects
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