Airfoil database search
Search the 1638 airfoils available in the databases filtering by name, thickness and camber. Click on an airfoil image to display a larger preview picture. There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers.
(goe561-il) GOE 561 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 561 airfoil Max thickness 25% at 29.8% chord Max camber 10.2% at 29.8% chord Source UIUC Airfoil Coordinates Database | |
(goe448-il) GOE 448 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 448 airfoil Max thickness 12.9% at 29.8% chord Max camber 10.5% at 39.8% chord Source UIUC Airfoil Coordinates Database | |
(e420-il) EPPLER 420 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Eppler E420 high lift airfoil Max thickness 14.3% at 22.8% chord Max camber 10.6% at 40.5% chord Source UIUC Airfoil Coordinates Database | |
(cp-140-050-gn) Cambered plate C=14% T=5% R=0.96 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file | |
 | HAWT pipe blade with coordinates based on top surface. Camber=14% Wall thickness=5% Radius=0.963 Max thickness 5.5% at 3.6% chord Max camber 12.2% at 47.7% chord Source Generated | |
(goe462-il) GOE 462 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 462 airfoil Max thickness 11% at 9.9% chord Max camber 13.4% at 29.9% chord Source UIUC Airfoil Coordinates Database | |
(cp-160-050-gn) Cambered plate C=16% T=5% R=0.86 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file | |
 | HAWT pipe blade with coordinates based on top surface. Camber=16% Wall thickness=5% Radius=0.861 Max thickness 5.2% at 3.4% chord Max camber 14.3% at 49.2% chord Source Generated | |
(goe531-il) GOE 531 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 531 airfoil Max thickness 13.8% at 19.5% chord Max camber 14.7% at 49.3% chord Source UIUC Airfoil Coordinates Database | |
(cp-180-050-gn) Cambered plate C=18% T=5% R=0.78 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file | |
 | HAWT pipe blade with coordinates based on top surface. Camber=18% Wall thickness=5% Radius=0.784 Max thickness 5% at 3.2% chord Max camber 16.4% at 49.3% chord Source Generated | |
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