Statements (15)
| Predicate | Object |
|---|---|
| gptkbp:instanceOf |
gptkb:airfoil
|
| gptkbp:airfoilFamily |
gptkb:NACA_6-series
|
| gptkbp:camberPosition |
40% chord from leading edge
|
| gptkbp:designedBy |
gptkb:NACA
|
| gptkbp:introducedIn |
1940s
|
| gptkbp:maximumCamber |
6% of chord
|
| gptkbp:optimizedFor |
laminar flow
|
| gptkbp:thickness |
9% of chord
|
| gptkbp:usedBy |
model aircraft
general aviation aircraft |
| gptkbp:usedFor |
aircraft wings
|
| gptkbp:usedIn |
aeronautical engineering
|
| gptkbp:bfsParent |
gptkb:NACA_6-series_airfoils
|
| gptkbp:bfsLayer |
7
|
| http://www.w3.org/2000/01/rdf-schema#label |
NACA 6609
|