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.
(rae5212-il) RAE(NPL) 5212 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | RAE(NPL) 5212 transonic airfoil Max thickness 11.9% at 35.5% chord Max camber 1.8% at 69.1% chord Max Cl/Cd 57.8 at Re# 200,000 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 57.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database | |
(rg149-il) RG 14 9% AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Rolf Girsberger RG 14 (9%) airfoil Max thickness 9% at 31% chord Max camber 1.6% at 36% chord Max Cl/Cd 57.7 at Re# 200,000 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 57.7 at Re# 200,000 Source NWTC National WInd Technology Center | |
(rc08b3-il) NASA/LANGLEY RC-08(B)3 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | NASA/Langley RC-08(B)3 rotorcraft airfoil Max thickness 8% at 37.8% chord Max camber 1.1% at 34.1% chord Max Cl/Cd 57.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database | |
(fauvel-il) FAUVEL 14% AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Fauvel 14% flying wing airfoil Max thickness 14% at 25.2% chord Max camber 2.5% at 25.2% chord Max Cl/Cd 57.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database | |
(rc1064c-il) NASA/LANGLEY RC10-64C AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | NASA/Langley 10-64C rotorcraft airfoil Max thickness 10% at 40% chord Max camber 1% at 35% chord Max Cl/Cd 57.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database | |
(goe777-il) GOE 777 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Gottingen 777 airfoil Max thickness 22% at 30% chord Max camber 5.9% at 30% chord Max Cl/Cd 57.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database | |
(naca24112-jf) NACA 24112 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file | |
![]() | NACA 24112 5 digit reflex airfoil Max thickness 12% at 29.4% chord Max camber 1.7% at 20.6% chord Max Cl/Cd 57.7 at Re# 200,000 Source Javafoil generated | |
(v23010-il) BOEING-VERTOL V23010-1.58 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Boeing-Vertol V23010-1.58 rotorcraft airfoil Max thickness 10.2% at 30% chord Max camber 1.8% at 15% chord Max Cl/Cd 57.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database |
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