Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(naca663218-il) NACA 66(3)-218		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(3)-218 airfoil Max thickness 18% at 45% chord Max camber 1.1% at 50% chord Max Cl/Cd 16.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e399-il) EPPLER 399 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E399 human powered aircraft airfoil Max thickness 14.8% at 29% chord Max camber 5.1% at 51.4% chord Max Cl/Cd 16.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s816-nr) NREL's S816 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S816 primary 21.0% Dia=30 to 50 m Re=4.0E+6 Clmax(S)=1.20 Clmax(R)=1.17 Restrained max lift coef Max thickness 21% at 39% chord Max camber 1.8% at 67.6% chord Max Cl/Cd 16.9 at Re# 50,000 Source NWTC National WInd Technology Center
(naca663418-il) NACA 66(3)-418		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(3)-418 airfoil Max thickness 18% at 44.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 16.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx78k140a20-il) FX 78-K-140 A/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 78-K-140 airfoil for use with flaps (K) A/20 Max thickness 14.1% at 43.5% chord Max camber 4.4% at 43.5% chord Max Cl/Cd 16.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(naca643418-il) NACA 64(3)-418		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(3)-418 airfoil Max thickness 17.9% at 34.8% chord Max camber 2.2% at 50% chord Max Cl/Cd 16.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ah94156-il) AH 94-156		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 94-156 airfoil Max thickness 15.6% at 39.6% chord Max camber 3.6% at 41.5% chord Max Cl/Cd 16.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e1230-il) EPPLER 1230 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1230 general aviation airfoil (Long-EZ and Defiant wing airfoil) Max thickness 17.4% at 30.9% chord Max camber 3.6% at 25.6% chord Max Cl/Cd 16.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e169-il) E169 (14.4%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E169 low Reynolds number airfoil Max thickness 14.4% at 26.5% chord Max camber 0% at 0% chord Max Cl/Cd 16.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e593-il) EPPLER 593 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E593 airfoil Max thickness 11.3% at 24.2% chord Max camber 4.6% at 29.2% chord Max Cl/Cd 16.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database