| タイトル | Robust Airfoil Optimization in High Resolution Design Space |
| 本文（外部サイト） | http://hdl.handle.net/2060/20030066156 |
| 著者（英） | Li, Wu; Padula, Sharon L. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2003-01-01 |
| 言語 | eng |
| 内容記述 | The robust airfoil shape optimization is a direct method for drag reduction over a given range of operating conditions and has three advantages: (1) it prevents severe degradation in the off-design performance by using a smart descent direction in each optimization iteration, (2) it uses a large number of B-spline control points as design variables yet the resulting airfoil shape is fairly smooth, and (3) it allows the user to make a trade-off between the level of optimization and the amount of computing time consumed. The robust optimization method is demonstrated by solving a lift-constrained drag minimization problem for a two-dimensional airfoil in viscous flow with a large number of geometric design variables. Our experience with robust optimization indicates that our strategy produces reasonable airfoil shapes that are similar to the original airfoils, but these new shapes provide drag reduction over the specified range of Mach numbers. We have tested this strategy on a number of advanced airfoil models produced by knowledgeable aerodynamic design team members and found that our strategy produces airfoils better or equal to any designs produced by traditional design methods. |
| NASA分類 | Aircraft Design, Testing and Performance |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/89942 |
