| タイトル | Aerodynamic characteristics of 2 NASA supercritical airfoils with different maximum thickness |
| 本文（外部サイト） | http://hdl.handle.net/2060/19840019599 |
| 著者（英） | Harris, C. D. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1972-04-01 |
| 言語 | eng |
| 内容記述 | Transonic wind tunnel tests were conducted at Mach numbers from 0.60 to 0.81 to determine the aerodynamic characteristics of two NASA supercritical airfoils. The airfoils had maximum thicknesses of 10 and 11 percent of the chord. Normal forces and pitching moments acting on the airfoils were determined from surface static pressure measurements. Drag forces acting on the airfoils were derived from vertical variations of the total and static pressures measured across the wake. For the thinner airfoil, stall begins at approximately 0.1 higher normal-force coefficient at the higher test Mach numbers, and the drag divergence Mach number at a normal-force coefficient of 0.7 was 0.01 higher. |
| NASA分類 | AERONAUTICS (GENERAL) |
| レポートNO | 84N27667
L-8173
NAS 1.15:2532
NASA-TM-X-2532 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/159160 |
