Airfoil Tools
Search 1638 airfoils

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Your Reynold number range is 50,000 to 1,000,000. (set)

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.

(goe410-il) GOE 410 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 410 airfoil Max thickness 16.1% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 35.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rae100-il) RAE 100 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 100 airfoil Max thickness 10% at 26% chord Max camber 0% at 0% chord Max Cl/Cd 35.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e1210-il) EPPLER 1210 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1210 general aviation airfoil Max thickness 15.9% at 21.1% chord Max camber 5.2% at 33.3% chord Max Cl/Cd 35.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e520-il) EPPLER 520 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E520 tailplane airfoil Max thickness 15% at 36.7% chord Max camber 0% at 0% chord Max Cl/Cd 35.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rae100-il) RAE 100 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 100 airfoil Max thickness 10% at 26% chord Max camber 0% at 0% chord Max Cl/Cd 35.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(raf30md-il) RAF 30 MOD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-30 MOD airfoil Max thickness 7.6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 35.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca653218-il) NACA 65(3)-218		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(3)-218 airfoil Max thickness 18% at 39.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 35.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx711530-il) FX 71-L-150/30 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 71-L-150/30 airfoil Max thickness 15% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 35.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx71l150-il) FX 71-L-150/30 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 71-L-150/30 airfoil Max thickness 15% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 35.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(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 Max Cl/Cd 35.2 at Re# 100,000 Source NWTC National WInd Technology Center