Apparatus and method for aircraft wing stall control
US5056741A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Sep 29, 1989 |
| Grant date | Oct 15, 1991 |
| Priority date | — |
| Expiry date | Sep 29, 2009 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/30
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An aircraft swept wing which provides pitch stability during stall conditions. In a swept wing aircraft which has leading edge flaps which in their deployed position forms a slot between the slot and the leading edge portion of a fixed main wing structure, the configuration of said leading edge portion is varied spanwise to vary the localized aerodynamic pressure spanwise along the wing. Increased bluntness of said leading edge portion, or increased slot-gap width, creates a stall condition on an inboard portion of the wing which approximates, at increasing angles of attack, the lift and pitching moment changes simultaneously experienced on outboard portions of the wing. As a result, adverse nose-up pitching moment under stall conditions is avoided, and improved pitch stability is achieved in swept wing aircraft, without compromising maximum lift capability.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.