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.
(s821-nr) NREL's S821 Airfoil | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file | |
 | NREL HAWT airfoil S821 root 24.0% Dia=10 to 20 m Re=8.0E+5 Clmax(S)=1.40 Clmax(R)=1.35 Restrained max lift coef Max thickness 24.2% at 24.6% chord Max camber 2.6% at 77.6% chord Max Cl/Cd 75.6 at Re# 1,000,000 Source NWTC National WInd Technology Center | |
(n0009sm-il) NACA-0009 9.0% smoothed | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | NACA 0009 airfoil (smoothed) Max thickness 9% at 30.9% chord Max camber 0% at 0% chord Max Cl/Cd 75.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(goe703-il) GOE 703 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 703 airfoil Max thickness 19.4% at 30% chord Max camber 2.3% at 30% chord Max Cl/Cd 75.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(ht22-il) HT22 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Drela HT22 airfoil Max thickness 5.1% at 19.1% chord Max camber 1.1% at 22.7% chord Max Cl/Cd 75.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(n0012-il) NACA 0012 AIRFOILS | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | NACA 0012 airfoil Max thickness 12% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 75.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(goe459-il) GOE 459 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 459 airfoil Max thickness 12.7% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 75.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(fx76100-il) WORTMANN FX 76-100 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Wortmann FX 76-100 symmetrical airfoil Max thickness 10.1% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 75.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(n5h20-il) NACA 5-H-20 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | NACA 5-H-20 rotorcraft airfoil Max thickness 19.9% at 40% chord Max camber 4.5% at 40% chord Max Cl/Cd 75.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(goe416a-il) GOE 416A AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 416A airfoil Max thickness 11.7% at 29.5% chord Max camber 1.3% at 59.6% chord Max Cl/Cd 75.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(goe575-il) GOE 575 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 575 airfoil Max thickness 13.3% at 29.8% chord Max camber 3.6% at 39.8% chord Max Cl/Cd 75.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
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