Integrated hypersonic inlet design
US8256706B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 8, 2009 |
| Grant date | Sep 4, 2012 |
| Priority date | — |
| Expiry date | Sep 5, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T137/0536
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
Methods, aircraft, and engine nacelles are disclosed. A wing leading edge of a planform is superimposed on a wing shockwave that extends in a first direction from a shockwave apex toward the wing leading edge. A waverider shape is streamline traced between the wing leading edge and a trailing edge of the planform to form a waverider wing. A position of an engine inlet vertex relative to the waverider wing is identified. An inlet shockwave is projected from the inlet vertex in a second direction generally opposed to the first direction. The inlet shockwave intersects the wing shockwave. An inlet leading edge of an engine inlet includes a lower leading edge including a plurality of points where the inlet shockwave intersects the wing shockwave.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.