Statements (16)
| Predicate | Object |
|---|---|
| gptkbp:instanceOf |
gptkb:airfoil
|
| gptkbp:camberPosition |
40% chord from leading edge
|
| gptkbp:camberType |
single camber
|
| gptkbp:designedBy |
gptkb:NACA
|
| gptkbp:designedFor |
laminar flow
|
| gptkbp:maximumCamber |
2% of chord
|
| gptkbp:series |
gptkb:NACA_6-series
|
| gptkbp:symmetry |
asymmetric
|
| gptkbp:thickness |
gptkb:NACA_6-series_formula
15% of chord |
| gptkbp:usedIn |
gptkb:aircraft_wing_design
aeronautical engineering |
| gptkbp:bfsParent |
gptkb:NACA_airfoil
gptkb:NACA_airfoil_series |
| gptkbp:bfsLayer |
7
|
| http://www.w3.org/2000/01/rdf-schema#label |
NACA 63-215
|