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.

(goe592-il) GOE 592 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 592 airfoil Max thickness 14.3% at 29.7% chord Max camber 7.5% at 39.7% chord Max Cl/Cd 45.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fxm2-il) WORTMANN FX M2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX M2 airfoil Max thickness 8.4% at 19.6% chord Max camber 4.8% at 30.9% chord Max Cl/Cd 45.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e338-il) EPPLER 338 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E338 flying wing airfoil Max thickness 13.3% at 31.1% chord Max camber 3.7% at 26.2% chord Max Cl/Cd 45.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh45-il) MH 45 9.85%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 45 for flying wings Max thickness 9.8% at 26.9% chord Max camber 1.7% at 36.6% chord Max Cl/Cd 45.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e1210-il) EPPLER 1210 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1210 general aviation airfoil Max thickness 15.9% at 21.1% chord Max camber 5.2% at 33.3% chord Max Cl/Cd 45.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(n64212-il) NACA 64(1)-212		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-212 airfoil Max thickness 12% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 45.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca64209-il) NACA 64-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-209 airfoil Max thickness 9% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 45.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(eh2012-il) EH 2.0/12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 2.0/12 for tailless R/C aircraft Max thickness 12% at 28.7% chord Max camber 2% at 25.9% chord Max Cl/Cd 45.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe553-il) GOE 553 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 553 airfoil Max thickness 13.7% at 29.6% chord Max camber 4.7% at 39.6% chord Max Cl/Cd 45.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e403-il) EPPLER 403 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E403 general purpose airfoil Max thickness 15% at 37.9% chord Max camber 3.2% at 75.5% chord Max Cl/Cd 45.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database