Plasma actuators for drag reduction on wings, nacelles and/or fuselage of vertical take-off and landing aircraft
US8308112B2 · kind B2 · utility
27Cited by
13References
23Claims
0Family size
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Key dates
| Filing date | Sep 13, 2006 |
| Grant date | Nov 13, 2012 |
| Priority date | — |
| Expiry date | Jun 15, 2027 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/10
- WIPO fieldChemical engineering
- WIPO sectorChemistry
Abstract
An aircraft includes a surface over which an airflow passes. A plasma actuator is configured to generate a plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of the airflow from the surface. A method of reducing separation of an airflow from a surface of an aircraft includes generating a plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.