| タイトル | Two experimental supercritical laminar-flow-control swept-wing airfoils |
| 本文（外部サイト） | http://hdl.handle.net/2060/19890009895 |
| 著者（英） | Dagenhart, J. Ray; Allison, Dennis O. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1987-02-01 |
| 言語 | eng |
| 内容記述 | Two supercritical laminar-flow-control airfoils were designed for a large-chord swept-wing experiment in the Langley 8-Foot Transonic Pressure Tunnel where suction was provided through most of the model surface for boundary-layer control. The first airfoil was derived from an existing full-chord laminar airfoil by extending the trailing edge and making changes in the two lower-surface concave regions. The second airfoil differed from the first one in that it was designed for testing without suction in the forward concave region of the lower surface. Differences between the first airfoil and the one from which it was derived as well as between the first and second airfoils are discussed. Airfoil coordinates and predicted pressure distributions for the design normal Mach number of 0.755 and section lift coefficient of 0.55 are given for the three airfoils. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 89N19266
NASA-TM-89073
NAS 1.15:89073 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/143074 |
