Statements (24)
| Predicate | Object |
|---|---|
| gptkbp:instanceOf |
gptkb:airfoil_family
|
| gptkbp:basisFor |
gptkb:NACA_6-series_airfoils
gptkb:NACA_5-series_airfoils |
| gptkbp:characterizedBy |
4-digit code
|
| gptkbp:codeFormat |
NACA MPXX
|
| gptkbp:developedBy |
gptkb:National_Advisory_Committee_for_Aeronautics
|
| gptkbp:example |
gptkb:NACA_0012
gptkb:NACA_2412 gptkb:NACA_4412 |
| gptkbp:introducedIn |
1930s
|
| gptkbp:notableFor |
simple mathematical description
widespread use in early aircraft |
| gptkbp:PP |
position of maximum camber (as tenths of chord)
|
| gptkbp:publishedIn |
gptkb:NACA_Technical_Reports
|
| gptkbp:usedFor |
wings
propellers control surfaces |
| gptkbp:usedIn |
gptkb:engineer
aeronautical engineering |
| gptkbp:XX |
maximum thickness (as % of chord)
|
| gptkbp:מטה |
maximum camber (as % of chord)
|
| gptkbp:bfsParent |
gptkb:NACA_6-series_airfoils
|
| gptkbp:bfsLayer |
7
|
| http://www.w3.org/2000/01/rdf-schema#label |
NACA 4-series airfoils
|