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.

(goe370-il) GOE 370 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 370 airfoil Max thickness 4.7% at 20% chord Max camber 5.7% at 40% chord Max Cl/Cd 121.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e214-il) E214 (11.1%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E214 low Reynolds number airfoil Max thickness 11.1% at 33.1% chord Max camber 3.7% at 56.9% chord Max Cl/Cd 121.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ah80129-il) AH 80-129		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 80-129 airfoil Max thickness 12.9% at 40.2% chord Max camber 4.1% at 43.5% chord Max Cl/Cd 121.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s1210-il) S1210 12%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1210 high lift low Reynolds number airfoil Max thickness 12% at 21.4% chord Max camber 6.7% at 51.1% chord Max Cl/Cd 121.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(miley-il) MILEY M06-13-128		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Miley MO6-13-128 airfoil Max thickness 12.9% at 35% chord Max camber 4.9% at 35% chord Max Cl/Cd 121.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(fx05h126-il) WORTMANN FX 05-H-126 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 05-H-126 rotorcraft airfoil Max thickness 12.6% at 37.1% chord Max camber 4.4% at 37.1% chord Max Cl/Cd 121.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e67-il) EPPLER 67 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E67 low Reynolds number airfoil Max thickness 11.6% at 32.6% chord Max camber 3.7% at 51.6% chord Max Cl/Cd 121.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe396-il) GOE 396 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 396 airfoil Max thickness 4.7% at 30% chord Max camber 5.8% at 40% chord Max Cl/Cd 121.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(dae51-il) DAE-51 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela DAE51 low Reynolds number airfoil Max thickness 9.4% at 30.7% chord Max camber 4% at 46.4% chord Max Cl/Cd 121.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ah88k130-il) AH 88-K-130/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 88-K-130/20 airfoil for use with flaps (K) Max thickness 13% at 43.5% chord Max camber 3.9% at 46.7% chord Max Cl/Cd 121.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database