Plasma actuators for drag reduction on wings, nacelles and/or fuselage of vertical take-off and landing aircraft

Patent

Description

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.

Attributes

Attribute NameValues
Title
  • Plasma actuators for drag reduction on wings, nacelles and/or fuselage of vertical take-off and landing aircraft

Patent Number
  • US 8308112 B2

USPTO Link
Inventor
  • Tommie L. Wood

  • Thomas C. Corke

  • Martiqua Post

Inventor From Local Institution
  • Thomas C. Corke

Other Application
  • 11/519,770

Prior Publication Date
  • 2010-09-09

Prior Publication Number
  • US 20100224733 A1

Claims
  • 23

Classification (US Patent)
  • 244/205; 244/203;

Cooperative Patent Classification codes
  • B64C 23/005 (20130101); F15D 1/12 (20130101); F05D 2270/172 (20130101); Y02T 50/166 (20130101); B64C 2230/12 (20130101)

International Patent Classification codes
  • B64C 21/00 (20060101); B64C 23/00 (20060101)

Language
  • eng

Date Issued
  • 2012-11-13

Publisher
  • United States Patent and Trademark Office

Assignee
  • University of Notre Dame Du Lac

  • Textron Innovations Inc. (Providence, RI)

Record Visibility and Access Public
Content License
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Collections Featuring this Patent
Notre Dame Patents

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