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.

(s814-nr) NREL's S814 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S814 root 24.0% Dia=20 to 30 m Re=1.5E+6 Clmax(S)=1.56 Clmax(R)=1.51 High max lift coef Max thickness 24.1% at 28.4% chord Max camber 3% at 74.5% chord Source NWTC National WInd Technology Center
(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 Source NWTC National WInd Technology Center
(naca4424-il) NACA 4424		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4424 airfoil Max thickness 24% at 29.4% chord Max camber 4% at 40% chord Source UIUC Airfoil Coordinates Database
(naca2424-il) NACA 2424		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2424 airfoil Max thickness 24% at 29.7% chord Max camber 2% at 40% chord Source UIUC Airfoil Coordinates Database
(naca23024-il) NACA 23024		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23024 airfoil Max thickness 24% at 30.3% chord Max camber 2.9% at 1.3% chord Source UIUC Airfoil Coordinates Database
(naca0024-il) NACA 0024		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0024 airfoil Max thickness 24% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(mh150-il) MH 150 23.89%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 150 for marine ruddershaft for torque reduction (schottel units) Max thickness 23.9% at 27.2% chord Max camber 4.5% at 53.8% chord Source UIUC Airfoil Coordinates Database
(goe434-il) GOE 434 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 434 airfoil Max thickness 22.8% at 28.4% chord Max camber 5.2% at 48.5% chord Source UIUC Airfoil Coordinates Database
(e858-il) EPPLER 858 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E858 propeller airfoil Max thickness 22.7% at 26.6% chord Max camber 4.7% at 44.3% chord Source UIUC Airfoil Coordinates Database
(fx83w227-il) FX 83-W-227		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 83-W-227 airfoil for use on wind turbines (W) Max thickness 22.6% at 33.9% chord Max camber 3.4% at 40.2% chord Source UIUC Airfoil Coordinates Database

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