| タイトル | A study of the drooped leading edge airfoil |
| 本文（外部サイト） | http://hdl.handle.net/2060/19790017842 |
| 著者（英） | Barlow, J. B.; Anderson, J. D., Jr. |
| 著者所属（英） | Maryland Univ. |
| 発行日 | 1979-04-01 |
| 言語 | eng |
| 内容記述 | Wind tunnel tests were conducted to examine various aspects of the drooped-leading edge airfoil which reduces the tendency for an airplane to enter a spin after stall occurs. Three baseline models were used for tests of two dimensional models: NACA 0015, 0014.6, and 0014.2. The 14.6% and 14.2% models were derived from NACA 0015 sections by increasing the chord and matching the profiles aft section. Force, balance data (lift, drag, pitching moment) were obtained for each model at a free-steam Reynold's number of 2.66 x 10 to the 6th power/m. In addition, oil flow visualization tests were performed at various angles of attack. An existing NACA 64 sub 1 A211 airfoil was used in a second series of tests. The leading edge flap was segmented in three parts which allowed various baseline/drooped leading edge configurations to be tested. Force balance and flow visualization tests were completer at chord Renolds numbers of 0.44 x 10 to the 6th power, 1.4 x 10 to the 6th power, and 2.11 x 10 to the 6th power. Test results are included. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 79N26013
NASA-CR-158717
SR-1 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/175235 |
|
