Electro-Magnetic Flow Control to Enable Natural Laminar Flow Wings

Metadata Updated: February 28, 2019

This research team has developed a solid-state electromagnetic device that, when embedded along the leading edge of an aircraft wing, can disrupt laminar air flow on command. The methodology employs a combination of high-voltage AC and DC electric fields and high-strength magnets to generate cross flow. This cross flow either forms vortices or trips the flow to turbulent (depending on conditions), energizing the boundary layer to keep the flow attached and prevent stall. Presumed usage would be for an aircraft to activate the device at take off, turn the device off after gear-up and initial climb-out, then turn back on for descent and landing. Using natural laminar flow principles in aircraft design can reduce fuel burn by 6 to 12 percent. Work to date: The device has been tested on a flat plate in a wind tunnel.  Looking ahead: In 2014, the group plans to test the device on a Dryden Remotely Operated Integrated Drone (DROID) aircraft and is targeting 2015 for tests on a Prototype Technology Evaluation Research Aircraft (PTERA).  Partner: Brigham Young University provides a wind tunnel and machining facilities to build test articles.    Benefits  Efficient: Enables fuel reduction  Simple: Works with no moving parts, simplifying fabrication and maintenance  Improves safety: Facilitates safer takeoffs and landings  Applications  Aircraft wings  Industrial fluid processing  Heat transfer processes This research aims to enable the use of high speed natural laminar flow airfoils by the addition of an electromagnetic flow control device. The device consists of an emitter wire and collection plate mounted flush on a wing surface, with magnets mounted between them, just below the surface. A high voltage signal is applied to the emitter wire while the collection plate is grounded, which sets up an electric field and ionizes the air. As the ions pass through the magnetic field, the Lorentz force directs flow along the wing span, creating vortices that prevent separation. The primary result of this project is an analytical model of the electromagnetic flow control device.

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Public: This dataset is intended for public access and use. License: U.S. Government Work

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Metadata Created Date August 1, 2018
Metadata Updated Date February 28, 2019

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Harvested from NASA Data.json

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Resource Type Dataset
Metadata Created Date August 1, 2018
Metadata Updated Date February 28, 2019
Publisher Space Technology Mission Directorate
Unique Identifier TECHPORT_10705
Maintainer
TECHPORT SUPPORT
Maintainer Email
Public Access Level public
Bureau Code 026:00
Metadata Context https://project-open-data.cio.gov/v1.1/schema/catalog.jsonld
Metadata Catalog ID https://data.nasa.gov/data.json
Schema Version https://project-open-data.cio.gov/v1.1/schema
Catalog Describedby https://project-open-data.cio.gov/v1.1/schema/catalog.json
Harvest Object Id 8556670b-fafc-48e6-9ea7-77f30f761c5e
Harvest Source Id 39e4ad2a-47ca-4507-8258-852babd0fd99
Harvest Source Title NASA Data.json
Data First Published 2012-10-01
Homepage URL https://techport.nasa.gov/view/10705
License http://www.usa.gov/publicdomain/label/1.0/
Data Last Modified 2018-07-19
Program Code 026:027
Source Datajson Identifier True
Source Hash e1e2c996411b515bb60cf2b3adfbbe4e685fb407
Source Schema Version 1.1

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