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.
(goe515-il) GOE 515 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 515 airfoil Max thickness 8.5% at 30% chord Max camber 2.8% at 40% chord Max Cl/Cd 119 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(goe414-il) GOE 414 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 414 airfoil Max thickness 13.6% at 29.7% chord Max camber 5.3% at 39.7% chord Max Cl/Cd 119 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(goe401-il) GOE 401 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 401 airfoil Max thickness 7.1% at 29.9% chord Max camber 4.9% at 29.9% chord Max Cl/Cd 119 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(fx61140-il) FX 61-140 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Wortmann FX 61-140 airfoil Max thickness 14% at 33.9% chord Max camber 2.5% at 30.9% chord Max Cl/Cd 119 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(fx05191-il) WORTMANN FX 05-191 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Wortmann FX 05-191 airfoil Max thickness 19.1% at 37.1% chord Max camber 2.6% at 50% chord Max Cl/Cd 118.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(s825-nr) NREL's S825 Airfoil | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file | |
 | NREL HAWT airfoil S825 primary 17.0% Dia=20 to 40 m Re=2.0E+6 Clmax(S)=1.44 Clmax(R)=1.37 High max lift coef Max thickness 17.1% at 29.9% chord Max camber 3.9% at 65.3% chord Max Cl/Cd 118.9 at Re# 1,000,000 Source NWTC National WInd Technology Center | |
(goe450-il) GOE 450 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 450 airfoil Max thickness 8.9% at 29.9% chord Max camber 5.2% at 39.9% chord Max Cl/Cd 118.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(goe187-il) GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 187 (Schatte-Lanz 2U10) airfoil Max thickness 8.3% at 30% chord Max camber 4.8% at 30% chord Max Cl/Cd 118.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(m24-il) NACA M24 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | NACA/Munk M-24 airfoil Max thickness 12% at 30.1% chord Max camber 6.3% at 30.1% chord Max Cl/Cd 118.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(boe106-il) BOEING 106 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Boeing 106 airfoil Max thickness 13.1% at 30% chord Max camber 3.3% at 40% chord Max Cl/Cd 118.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
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