| タイトル | Experimental study of wing leading-edge devices for improved maneuver performance of a supercritical maneuvering fighter configuration |
| 本文（外部サイト） | http://hdl.handle.net/2060/19830013891 |
| 著者（英） | Fox, C. H., Jr.; Mann, M. J.; Campbell, R. L.; Huffman, J. K. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1983-03-01 |
| 言語 | eng |
| 内容記述 | Wind tunnel tests were conducted to examine the use of wing leading-edge devices for improved subsonic and transonic maneuver performance. These devices were tested on a fighter configuration which utilized supercritical-wing technology. The configuration had a leading-edge sweep of 45 deg and an aspect ratio of 3.28. The tests were conducted at Mach numbers of 0.60 and 0.85 with angles of attack from -0.5 deg to 22 deg. At both Mach numbers, sharp leading-edge flaps produced vortices which greatly altered the flow pattern on the wing and resulted in substantial reductions in drag at high lift. Underwing or pylon-type vortex generators also reduced drag at high lift. The vortex generators worked better at a Mach number of 0.60. The vortex generators gave the best overall results with zero toe-in angle and when mounted on either the outboard part of the wing or at both an outboard location and halfway out the semispan. Both the flaps and the vortex generators had a minor effect on the pitching moment. Fluorescent minitufts were found to be useful for flow visualization at transonic maneuver conditions. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 83N22162
NASA-TP-2125
NAS 1.60:2125
L-15539 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/162956 |
