| タイトル | Aerodynamic performance and pressure distributions for a NASA SC(2)-0714 airfoil tested in the Langley 0.3-meter transonic cryogenic tunnel |
| 本文（外部サイト） | http://hdl.handle.net/2060/19880015196 |
| 著者（英） | Jenkins, Renaldo V.; Hill, Acquilla S.; Ray, Edward J. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1988-07-01 |
| 言語 | eng |
| 内容記述 | This report presents in graphic and tabular forms the aerodynamic coefficient and surface pressure distribution data for a NASA SC(2)-0714 airfoil tested in the Langley 0.3-Meter Transonic Cryogenic Tunnel. The test was another in a series of tests involved in the joint NASA/U.S. Industry Advanced Technology Airfoil Tests program. This 14% thick supercritical airfoil was tested at Mach numbers from 0.6 to 0.76 and angles of attack from -2.0 to 6.0 degrees. The test Reynolds numbers were 4 million, 6 million, 10 million, 15 million, 30 million, 40 million, and 45 million. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 88N24580
NAS 1.15:4044
NASA-TM-4044
L-16384 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/146057 |
