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.
(naca652415-il) NACA 65(2)-415 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | NACA 65(2)-415 airfoil Max thickness 15% at 39.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 105.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(mh120-il) MH 120 11.57% | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Martin Hepperle MH 120 for tip section of a propeller Max thickness 11.6% at 34.7% chord Max camber 2.2% at 44.2% chord Max Cl/Cd 105.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(s818-nr) NREL's S818 Airfoil | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file | |
![]() | NREL HAWT airfoil S818 root 24.0% Dia=30 to 50 m Re=2.5E+6 Clmax(S)=1.68 Clmax(R)=1.61 Restrained max lift coef Max thickness 24% at 30.9% chord Max camber 3.3% at 74.2% chord Max Cl/Cd 105.9 at Re# 1,000,000 Source NWTC National WInd Technology Center | |
(goe647-il) GOE 647 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Gottingen 647 airfoil Max thickness 16.2% at 19.5% chord Max camber 5.3% at 39.4% chord Max Cl/Cd 105.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(naca654221-il) NACA 65(4)-221 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | NACA 65(4)-221 airfoil Max thickness 21% at 39.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 105.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(hq359-il) HQ 3.5/9 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Quabeck HQ 3.5/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 3.5% at 50% chord Max Cl/Cd 105.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(e850-il) EPPLER E850 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Eppler E850 propeller airfoil Max thickness 8% at 36.6% chord Max camber 1.8% at 71% chord Max Cl/Cd 105.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(mb253515sm-il) MB253515 15.0% smoothed | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Mike Bame MB253515 low Reynolds number airfoil Max thickness 15% at 35% chord Max camber 2.5% at 37.5% chord Max Cl/Cd 105.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(sd6060-il) SD6060-104-88 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Selig/Donovan SD6060 low Reynolds number airfoil Max thickness 10.4% at 33.9% chord Max camber 1.6% at 38.6% chord Max Cl/Cd 105.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database | |
(goe802b-il) GOE 802 B AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Gottingen 802 B airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 105.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database |
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