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.

(k3-il) GRUMMAN K-3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman K-3 transonic airfoil (GAC .70-.83-17.5) Max thickness 17.3% at 33.1% chord Max camber 2.6% at 74.7% chord Max Cl/Cd 33.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx711520-il) FX 71-L-150/20 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-150/20 airfoil Max thickness 15% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 33.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sc20706-il) NASA SC(2)-0706 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0706 airfoil (NASA TP-2969) Max thickness 6% at 34% chord Max camber 1.6% at 82% chord Max Cl/Cd 33.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe386-il) GOE 386 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 386 airfoil Max thickness 20.3% at 29% chord Max camber 5.4% at 39% chord Max Cl/Cd 33.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e664-il) EPPLER 664 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E664 variable geometry sailplane airfoil Max thickness 16.6% at 45.6% chord Max camber 2.6% at 40.7% chord Max Cl/Cd 33.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(fx77080-il) WORTMANN FX 77-080		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 77-080 symmetrical airfoil Max thickness 8% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 33.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(nacam2-il) NACA M2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA M2 airfoil Max thickness 8.1% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 33.2 at Re# 100,000 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 Max Cl/Cd 33.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s829-nr) NREL's S829 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S829 tip 16.0% Dia=20 to 40 m Re=2.0E+6 Clmax(S)=0.70 Clmax(R)=0.68 Restrained max lift coef Max thickness 16% at 48.3% chord Max camber 0.7% at 48.3% chord Max Cl/Cd 33.1 at Re# 100,000 Source NWTC National WInd Technology Center
(sc20012-il) NASA SC(2)-0012 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0012 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 0% at 0% chord Max Cl/Cd 33.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database