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.
(s1221-il) S1221 w/o flap | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Selig S1221 airfoil Max thickness 12.1% at 21.8% chord Max camber 4.9% at 49.1% chord Max Cl/Cd 137.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(fx6617ai-il) WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Wortmann FX 66-17AII-182 airfoil (as tested at NASA) Max thickness 18.8% at 35.3% chord Max camber 3.7% at 40.2% chord Max Cl/Cd 137.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(ah63k127-il) AH 63-K-127/24 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Althaus AH 63-K-127/24 airfoil for use with flaps (K) Max thickness 12.7% at 40.2% chord Max camber 3.8% at 43.5% chord Max Cl/Cd 137.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(goe412-il) GOE 412 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 412 airfoil Max thickness 13.1% at 29.7% chord Max camber 5.1% at 39.7% chord Max Cl/Cd 137.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(goe528-il) GOE 528 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 528 airfoil Max thickness 12.5% at 29.8% chord Max camber 6.2% at 39.8% chord Max Cl/Cd 137.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(s826-nr) NREL's S826 Airfoil | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file | |
 | NREL HAWT airfoil S826 tip 14.0% Dia=20 to 40 m Re=1.5E+6 Clmax(S)=1.42 Clmax(R)=1.31 High max lift coef Max thickness 14% at 33.7% chord Max camber 4.3% at 62% chord Max Cl/Cd 137.7 at Re# 1,000,000 Source NWTC National WInd Technology Center | |
(goe234-il) GOE 234 (MVA CA5) AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Gottingen 234 (MVA CA5) airfoil Max thickness 14.2% at 19.7% chord Max camber 9.2% at 49.7% chord Max Cl/Cd 137.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(fx63137sm-il) FX 63-137 13.7% smoothed | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Wortmann FX 63-137 airfoil (smoothed) Max thickness 13.7% at 30.9% chord Max camber 5.8% at 56.5% chord Max Cl/Cd 137.6 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 137.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(ah82150a-il) AH 82-150 A | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
 | Althaus AH 82-150 A airfoil Max thickness 15% at 40.2% chord Max camber 3.3% at 43.5% chord Max Cl/Cd 137.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
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