| タイトル | Natural laminar flow airfoil design considerations for winglets on low-speed airplanes |
| 本文（外部サイト） | http://hdl.handle.net/2060/19850004555 |
| 著者（英） | Vandam, C. P. |
| 著者所属（英） | Vigyan Research Associates, Inc. |
| 発行日 | 1984-12-01 |
| 言語 | eng |
| 内容記述 | Winglet airfoil section characteristics which significantly influence cruise performance and handling qualities of an airplane are discussed. A good winglet design requires an airfoil section with a low cruise drag coefficient, a high maximum lift coefficient, and a gradual and steady movement of the boundary layer transition location with angle of attack. The first design requirement provides a low crossover lift coefficient of airplane drag polars with winglets off and on. The other requirements prevent nonlinear changes in airplane lateral/directional stability and control characteristics. These requirements are considered in the design of a natural laminar flow airfoil section for winglet applications and chord Reynolds number of 1 to 4 million. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 85N12863
NASA-CR-3853
NAS 1.26:3853 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/157806 |
