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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.

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(rae5212-il) RAE(NPL) 5212 AIRFOIL

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RAE(NPL) 5212 AIRFOILRAE(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

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GOE 416A AIRFOILGottingen 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

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RG 14 9% AIRFOILRolf 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

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NREL's S818 AirfoilNREL 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

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NASA/LANGLEY RC-08(B)3 AIRFOILNASA/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

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FAUVEL 14% AIRFOILFauvel 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

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NASA/LANGLEY RC10-64C AIRFOILNASA/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

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GOE 777 AIRFOILGottingen 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

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NACA 24112NACA 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

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BOEING-VERTOL V23010-1.58 AIRFOILBoeing-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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