| タイトル | Characteristics of wake vortex generated by a Boeing 727 jet transport during two-segment and normal ILS approach flight paths |
| 本文（外部サイト） | http://hdl.handle.net/2060/19760014087 |
| 著者（英） | Kurkowski, R. L.; Garodz, L. J.; Barber, M. R. |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 1976-04-01 |
| 言語 | eng |
| 内容記述 | A series of flight tests was conducted to evaluate the vortex wake characteristics of a Boeing 727 (B727-200) aircraft during conventional and two-segment ILS approaches. Twelve flights of the B727, which was equipped with smoke generators for vortex marking, were flown and its vortex wake was intentionally encountered by a Lear Jet model 23 (LR-23) and a Piper Twin Comanche (PA-30). Location of the B727 vortex during landing approach was measured using a system of photo-theodolites. The tests showed that at a given separation distance there were no readily apparent differences in the upsets resulting from deliberate vortex encounters during the two types of approaches. Timed mappings of the position of the landing configuration vortices showed that they tended to descend approximately 91 m(300 ft) below the flight path of the B727. The flaps of the B727 have a dominant effect on the character of the trailed wake vortex. The clean wing produces a strong, concentrated vortex but as the flaps are lowered, the vortex system becomes more diffuse. Pilot opinion and roll acceleration data indicate that 4.5 n.mi. would be a minimum separation distance at which roll control of light aircraft (less than 5,670 kg (12,500 lb) could be maintained during parallel encounters of the B727's landing configuration wake. This minimum separation distance is generally in scale with results determined from previous tests of other aircraft using the small roll control criteria. |
| NASA分類 | AIR TRANSPORTATION AND SAFETY |
| レポートNO | 76N21175
A-6208
NASA-TN-D-8222 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/186425 |
