Statements (15)
| Predicate | Object |
|---|---|
| gptkbp:instanceOf |
gptkb:airfoil
|
| gptkbp:application |
aircraft wings
propeller blades |
| gptkbp:camber |
0% (symmetric)
|
| gptkbp:developedBy |
gptkb:NACA
|
| gptkbp:maximumThicknessLocation |
30% chord from leading edge
|
| gptkbp:notableFeature |
laminar flow design
low drag at high speeds |
| gptkbp:publishedBy |
gptkb:National_Advisory_Committee_for_Aeronautics
|
| gptkbp:series |
gptkb:NACA_16-series
|
| gptkbp:thickness |
12% of chord
|
| gptkbp:usedIn |
aeronautical engineering
|
| gptkbp:bfsParent |
gptkb:NACA_airfoil_series
|
| gptkbp:bfsLayer |
7
|
| https://www.w3.org/2000/01/rdf-schema#label |
NACA 16-012
|