| タイトル | Wind-tunnel results for an improved 21-percent-thick low-speed airfoil section |
| 本文（外部サイト） | http://hdl.handle.net/2060/19800012810 |
| 著者（英） | Beasley, W. D.; Mcghee, R. J. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1978-04-01 |
| 言語 | eng |
| 内容記述 | Low speed wind tunnel tests were conducted to evaluate the effects on performance of modifying a 23 percent thick low speed airfoil. The airfoil contour was altered to reduce the upper-surface adverse pressure gradient and hence reduce boundary layer separation. The chord Reynolds number varied from about 2,000,000 to 9,000,000. |
| NASA分類 | AIR TRANSPORTATION AND SAFETY |
| レポートNO | 80N21295
NASA-TM-78650
L-11970 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/172911 |
