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.

(e397-il) EPPLER 397 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E397 human powered aircraft airfoil Max thickness 13.5% at 29.4% chord Max camber 5.3% at 52.1% chord Max Cl/Cd 26.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe55-il) GOE 55 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 55 airfoil Max thickness 6.2% at 14.9% chord Max camber 2% at 19.9% chord Max Cl/Cd 26.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n2415-il) NACA 2415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2415 airfoil Max thickness 15% at 29.5% chord Max camber 2% at 39.6% chord Max Cl/Cd 26.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca64a010-il) NACA 64A-010 10.0%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64A010 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 26.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca651212-il) NACA 65(1)-212		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(1)-212 airfoil Max thickness 12% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 26.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(oa212-il) ONERA OA212 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OA212 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 12% at 31.8% chord Max camber 2.3% at 31.8% chord Max Cl/Cd 26.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s1012-il) S1012		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1012 HPV airfoil Max thickness 12% at 37.3% chord Max camber 0% at 0% chord Max Cl/Cd 26.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rae104-il) RAE 104 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 104 airfoil Max thickness 10% at 42% chord Max camber 0% at 0% chord Max Cl/Cd 26.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe303-il) GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 303 (Friedrichshafen G03) airfoil Max thickness 9.8% at 29.9% chord Max camber 5.9% at 39.9% chord Max Cl/Cd 26.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(nacam18-il) NACA M18		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA M18 airfoil Max thickness 12% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 26.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database