| タイトル | Euler technology assessment for preliminary aircraft design employing OVERFLOW code with multiblock structured-grid method |
| 本文（外部サイト） | http://hdl.handle.net/2060/19950016678 |
| 著者（英） | Muilenburg, Dennis A.; Treiber, David A. |
| 著者所属（英） | Boeing Defense and Space Group |
| 発行日 | 1995-03-01 |
| 言語 | eng |
| 内容記述 | The viability of applying a state-of-the-art Euler code to calculate the aerodynamic forces and moments through maximum lift coefficient for a generic sharp-edge configuration is assessed. The OVERFLOW code, a method employing overset (Chimera) grids, was used to conduct mesh refinement studies, a wind-tunnel wall sensitivity study, and a 22-run computational matrix of flow conditions, including sideslip runs and geometry variations. The subject configuration was a generic wing-body-tail geometry with chined forebody, swept wing leading-edge, and deflected part-span leading-edge flap. The analysis showed that the Euler method is adequate for capturing some of the non-linear aerodynamic effects resulting from leading-edge and forebody vortices produced at high angle-of-attack through C(sub Lmax). Computed forces and moments, as well as surface pressures, match well enough useful preliminary design information to be extracted. Vortex burst effects and vortex interactions with the configuration are also investigated. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 95N23095
NASA-CR-4651
NAS 1.26:4651 |
| 権利 | No Copyright |
|
