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.

(e715-il) EPPLER 715 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E715 tailplane airfoil Max thickness 15% at 33.1% chord Max camber 2.8% at 42% chord Max Cl/Cd 15.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mue139-il) MUE 139		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	MUE 139 airfoil Max thickness 13.9% at 22.2% chord Max camber 4.7% at 30.9% chord Max Cl/Cd 15.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe08k-il) GOE 8K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 8K airfoil Max thickness 14.9% at 50% chord Max camber 6.1% at 50% chord Max Cl/Cd 15.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca654221-il) NACA 65(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(4)-221 airfoil Max thickness 21% at 39.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 15.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e339-il) EPPLER 339 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E339 flying wing airfoil Max thickness 13.5% at 30.1% chord Max camber 4.1% at 25.2% chord Max Cl/Cd 15.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(ah93156-il) AH 93-156		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-156 airfoil Max thickness 15.7% at 39.5% chord Max camber 3.7% at 41.5% chord Max Cl/Cd 15.6 at Re# 50,000 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 15.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(cp-140-050-gn) Cambered plate C=14% T=5% R=0.96		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	HAWT pipe blade with coordinates based on top surface. Camber=14% Wall thickness=5% Radius=0.963 Max thickness 5.5% at 3.6% chord Max camber 12.2% at 47.7% chord Max Cl/Cd 15.6 at Re# 50,000 Source Generated
(npl9510-il) NPL 9510 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9510 transonic airfoil Max thickness 11.1% at 32% chord Max camber 1.6% at 80% chord Max Cl/Cd 15.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s809-nr) NREL's S809 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S809 primary 21.0% Re=2.0E+6 Clmax(S)=1.00 Restrained max lift coef Max thickness 21% at 39.5% chord Max camber 1% at 82.3% chord Max Cl/Cd 15.5 at Re# 50,000 Source NWTC National WInd Technology Center