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Pneumatic Spoiler Controls Airfoil LiftAir ejection from leading edge of airfoil used for controlled decrease of lift. Pneumatic-spoiler principle developed for equalizing lift on helicopter rotor blades. Also used to enhance aerodynamic control of short-fuselage or rudderless aircraft such as "flying-wing" airplanes. Leading-edge injection increases maneuverability of such high-performance fixed-wing aircraft as fighters.
Document ID
19910000594
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Hunter, D.
(United Technologies Corp.)
Krauss, T.
(United Technologies Corp.)
Date Acquired
August 14, 2013
Publication Date
November 1, 1991
Publication Information
Publication: NASA Tech Briefs
Volume: 15
Issue: 11
ISSN: 0145-319X
Subject Category
Mechanics
Report/Patent Number
ARC-11519
Accession Number
91B10594
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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