| タイトル | The cryogenic wind tunnel concept for high Reynolds number testing |
| 本文（外部サイト） | http://hdl.handle.net/2060/19750003928 |
| 著者（英） | Adcock, J. B.; Davenport, E. E.; Kilgore, R. A.; Goodyer, M. J. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1974-11-01 |
| 言語 | eng |
| 内容記述 | Theoretical considerations indicate that cooling the wind-tunnel test gas to cryogenic temperatures will provide a large increase in Reynolds number with no increase in dynamic pressure while reducing the tunnel drive-power requirements. Studies were made to determine the expected variations of Reynolds number and other parameters over wide ranges of Mach number, pressure, and temperature, with due regard to avoiding liquefaction. Practical operational procedures were developed in a low-speed cryogenic tunnel. Aerodynamic experiments in the facility demonstrated the theoretically predicted variations in Reynolds number and drive power. The continuous-flow-fan-driven tunnel is shown to be particularly well suited to take full advantage of operating at cryogenic temperatures. |
| NASA分類 | RESEARCH AND SUPPORT FACILITIES (AIR) |
| レポートNO | 75N12000
L-9396
NASA-TN-D-7762 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/192121 |
