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.
(clarkk-il) CLARK K AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | CLARK K airfoil Max thickness 11.7% at 29.7% chord Max camber 3.3% at 39.6% chord Max Cl/Cd 121.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(goe482-il) GOE 482 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 482 airfoil Max thickness 16.5% at 29.6% chord Max camber 8.8% at 39.6% chord Max Cl/Cd 121.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(e642-il) EPPLER 642 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Eppler E642 sailplane airfoil Max thickness 15.1% at 39.4% chord Max camber 3% at 39.4% chord Max Cl/Cd 121.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(s1223-il) S1223 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Selig S1223 high lift low Reynolds number airfoil Max thickness 12.1% at 19.8% chord Max camber 8.1% at 49% chord Max Cl/Cd 121.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(s816-nr) NREL's S816 Airfoil | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file | |
 | NREL HAWT airfoil S816 primary 21.0% Dia=30 to 50 m Re=4.0E+6 Clmax(S)=1.20 Clmax(R)=1.17 Restrained max lift coef Max thickness 21% at 39% chord Max camber 1.8% at 67.6% chord Max Cl/Cd 121.4 at Re# 1,000,000 Source NWTC National WInd Technology Center | |
(hor12-il) ONERA HOR12 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Onera propeller blade airfoils from US Patent 4 Max thickness 11.9% at 22.8% chord Max camber 3.7% at 46.2% chord Max Cl/Cd 121.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(goe190-il) GOE 190 (MVA MK.18) AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 190 (MVA MK.18) airfoil Max thickness 12.7% at 19.7% chord Max camber 5.9% at 49.7% chord Max Cl/Cd 121.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(s4061-il) S4061-096-84 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Selig S4061 low Reynolds number airfoil Max thickness 9.6% at 30.9% chord Max camber 3.3% at 44.7% chord Max Cl/Cd 121.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(s4233-il) S4233-136-84 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Selig S4233 low Reynolds number airfoil Max thickness 13.6% at 34.9% chord Max camber 2.7% at 48.8% chord Max Cl/Cd 121.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(goe428-il) GOE 428 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 428 airfoil Max thickness 7.9% at 30% chord Max camber 5.2% at 40% chord Max Cl/Cd 121.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
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