NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login

Press Enter or click the Search button to begin your search.

Back to Results
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
Report Number: ARC-11519
ISSN: 0145-319X
Accession Number
91B10594
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Available Downloads

There are no available downloads for this record.

Related Records

There are no records associated with this record.
No Preview Available