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The Effectiveness at High Speeds of a 20-Percent-chord Plain Trailing-edge Flap on the NACA 65-210 Airfoil SectionAn analysis has been made of the lift-control effectiveness of a 20-percent-chord plain trailing-edge flap on the NACA 65-210 airfoil section from section lift-coefficient data obtained at Mach numbers from 0.3 to 0.875. In addition, the effectiveness of the plain flap as a lift-control device has been compared with the corresponding effectiveness of both a spoiler and a dive-recovery flag on the INCA 65-210 airfoil section.
Document ID
20090025473
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Stivers, Louis S., Jr. (National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Date Acquired
August 24, 2013
Publication Date
May 6, 1947
Subject Category
Aerodynamics
Report/Patent Number
NACA-RM-SA7A17
Report Number: NACA-RM-SA7A17
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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