Laminar flow wing optimized for transonic cruise aircraft
US8448893B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 25, 2011 |
| Grant date | May 28, 2013 |
| Priority date | — |
| Expiry date | Dec 9, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/10
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
Aircraft configured to operate at Mach numbers from above 0.80 and up to 1.2 with wing sweep angles defined by the wing outboard leading edge of less than 35 degrees, and incorporating calculated values of the ratio of outboard wing panel aspect ratio raised to an exponent of 0.78, divided by the ratio of maximum thickness divided by chord (t/c), greater than about 45, characterized by one of the following: a) where maximum thickness divided by chord (t/c) is at a location approximately 70% of the distance outboard from the attaching aircraft body to the wing tip, or b) where maximum thickness divided by chord (t/c) is the average value of (t/c)'s located between approximately 50% of the distance outboard from the attaching aircraft body to the wing tip.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.