|
gptkbp:instanceOf
|
airfoil series
|
|
gptkbp:airfoilType
|
symmetric
cambered
|
|
gptkbp:application
|
model aircraft
propeller blades
wind turbine blades
full-scale aircraft
|
|
gptkbp:basisFor
|
gptkb:NACA_6-series
gptkb:NACA_7-series
gptkb:NACA_8-series
gptkb:NACA_5-series
|
|
gptkbp:countryOfOrigin
|
gptkb:United_States
|
|
gptkbp:developedBy
|
gptkb:National_Advisory_Committee_for_Aeronautics
|
|
gptkbp:feature
|
constant thickness distribution
easy to manufacture
linear camber line
no reflexed trailing edge
well-documented performance
|
|
gptkbp:form
|
defined by simple equations
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
NACA 4-series
|
|
gptkbp:introducedIn
|
1930s
|
|
gptkbp:namingConvention
|
NACA MPXX
|
|
gptkbp:notableExample
|
gptkb:NACA_0012
gptkb:NACA_2412
gptkb:NACA_4412
|
|
gptkbp:PP
|
location of maximum camber in tenths of chord
|
|
gptkbp:usedBy
|
gptkb:NASA
aerospace industry
|
|
gptkbp:usedFor
|
aircraft wing design
|
|
gptkbp:usedIn
|
aeronautical engineering
|
|
gptkbp:XX
|
maximum thickness as percentage of chord
|
|
gptkbp:מטה
|
maximum camber as percentage of chord
|
|
gptkbp:bfsParent
|
gptkb:NACA_6-series
gptkb:NACA_7-series
|
|
gptkbp:bfsLayer
|
7
|