| タイトル | Low-speed wind tunnel results for a modified 13-percent-thick airfoil |
| 本文（外部サイト） | http://hdl.handle.net/2060/19790016789 |
| 著者（英） | Mcghee, R. J.; Beasley, W. D. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1977-05-01 |
| 言語 | eng |
| 内容記述 | Wind-tunnel tests were conducted to evaluate the effects on performance of modifying a 13-percent-thick low-speed airfoil. The airfoil contour was altered to reduce the aft upper surface pressure gradient and hence delay boundary layer separation at typical lift coefficients for light general aviation airplanes. The tests were conducted at a Mach number of 0.15 or less over a Reynolds number range from about 1,000,000 to 9,000,000. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 79N24960
NASA-TM-X-74018 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/175417 |
