Statements (19)
| Predicate | Object |
|---|---|
| gptkbp:instanceOf |
gptkb:airfoil
|
| gptkbp:application |
general aviation
model aircraft |
| gptkbp:camberType |
cambered
|
| gptkbp:countryOfOrigin |
gptkb:United_States
|
| gptkbp:designedBy |
gptkb:NACA
|
| gptkbp:firstPublished |
1940s
|
| gptkbp:maximumCamber |
4% of chord
|
| gptkbp:maximumCamberPosition |
40% of chord from leading edge
|
| gptkbp:series |
gptkb:NACA_6-series
|
| gptkbp:symmetry |
asymmetric
|
| gptkbp:thickness |
gptkb:NACA_6-series_formula
12% of chord |
| gptkbp:usedFor |
propeller blades
wing design |
| gptkbp:usedIn |
aeronautical engineering
|
| gptkbp:bfsParent |
gptkb:NACA_6-series_airfoils
|
| gptkbp:bfsLayer |
7
|
| http://www.w3.org/2000/01/rdf-schema#label |
NACA 6412
|