| タイトル | A Comparative Study Using CFD to Predict Iced Airfoil Aerodynamics |
| 本文（外部サイト） | http://hdl.handle.net/2060/20050185210 |
| 著者（英） | Chi, x.; Li, Y.; Shih, T. I-P.; Choo, Y. K.; Chen, H.; Addy, H. E. |
| 著者所属（英） | NASA Glenn Research Center |
| 発行日 | 2005-03-08 |
| 言語 | eng |
| 内容記述 | WIND, Fluent, and PowerFLOW were used to predict the lift, drag, and moment coefficients of a business-jet airfoil with a rime ice (rough and jagged, but no protruding horns) and with a glaze ice (rough and jagged end has two or more protruding horns) for angles of attack from zero to and after stall. The performance of the following turbulence models were examined by comparing predictions with available experimental data. Spalart-Allmaras (S-A), RNG k-epsilon, shear-stress transport, v(sup 2)-f, and a differential Reynolds stress model with and without non-equilibrium wall functions. For steady RANS simulations, WIND and FLUENT were found to give nearly identical results if the grid about the iced airfoil, the turbulence model, and the order of accuracy of the numerical schemes used are the same. The use of wall functions was found to be acceptable for the rime ice configuration and the flow conditions examined. For rime ice, the S-A model was found to predict accurately until near the stall angle. For glaze ice, the CFD predictions were much less satisfactory for all turbulence models and codes investigated because of the large separated region produced by the horns. For unsteady RANS, WIND and FLUENT did not provide better results. PowerFLOW, based on the Lattice Boltzmann method, gave excellent results for the lift coefficient at and near stall for the rime ice, where the flow is inherently unsteady. |
| NASA分類 | Fluid Mechanics and Thermodynamics |
| レポートNO | AIAA Paper 2005-1371 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/219912 |
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