| タイトル | Application of a Navier-Stokes Solver to the Analysis of Multielement Airfoils and Wings Using Multizonal Grid Techniques |
| 本文（外部サイト） | http://hdl.handle.net/2060/19970013280 |
| 著者（英） | Jones, Kenneth M.; Whitlock, Mark; Biedron, Robert T. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1995-06-22 |
| 言語 | eng |
| 内容記述 | A computational study was performed to determine the predictive capability of a Reynolds averaged Navier-Stokes code (CFL3D) for two-dimensional and three-dimensional multielement high-lift systems. Three configurations were analyzed: a three-element airfoil, a wing with a full span flap and a wing with a partial span flap. In order to accurately model these complex geometries, two different multizonal structured grid techniques were employed. For the airfoil and full span wing configurations, a chimera or overset grid technique was used. The results of the airfoil analysis illustrated that although the absolute values of lift were somewhat in error, the code was able to predict reasonably well the variation with Reynolds number and flap position. The full span flap analysis demonstrated good agreement with experimental surface pressure data over the wing and flap. Multiblock patched grids were used to model the partial span flap wing. A modification to an existing patched- grid algorithm was required to analyze the configuration as modeled. Comparisons with experimental data were very good, indicating the applicability of the patched-grid technique to analyses of these complex geometries. |
| NASA分類 | Fluid Mechanics and Heat Transfer |
| レポートNO | 97N17202
NASA-TM-112005
NAS 1.15:112005
AIAA Paper 95-1855 |
| 権利 | No Copyright |
