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.

(coanda3-il) Coanda 3		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Coanda 3 airfoil Max thickness 7% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 75.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe533-il) GOE 533 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 533 airfoil Max thickness 13.7% at 30% chord Max camber 4.7% at 40% chord Max Cl/Cd 75.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe528-il) GOE 528 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 528 airfoil Max thickness 12.5% at 29.8% chord Max camber 6.2% at 39.8% chord Max Cl/Cd 75.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e212-il) E212 (10.55%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E212 low Reynolds number airfoil Max thickness 10.6% at 27.5% chord Max camber 2.5% at 61.3% chord Max Cl/Cd 75.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(m19-il) NACA M19 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-19 airfoil Max thickness 6.2% at 30% chord Max camber 6% at 30% chord Max Cl/Cd 75.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(s7055-il) S7055 (10.5%) Flat-Bottomed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S7055 low Reynolds number airfoil Max thickness 10.5% at 31.8% chord Max camber 3.3% at 38.6% chord Max Cl/Cd 75.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe335-il) GOE 335 (D.F.W.) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 335 (D.F.W.) airfoil Max thickness 6.9% at 20% chord Max camber 4.8% at 40% chord Max Cl/Cd 75.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(m14-il) NACA M14 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-14 airfoil Max thickness 8.1% at 30% chord Max camber 3.9% at 30% chord Max Cl/Cd 75.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e432-il) EPPLER 432 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E432 sailplane airfoil Max thickness 16% at 37.4% chord Max camber 4.5% at 37.4% chord Max Cl/Cd 75.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e682-il) EPPLER 682 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E682 sailplane airfoil Max thickness 15.3% at 40.4% chord Max camber 2.9% at 40.4% chord Max Cl/Cd 75.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database