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.

(mh108-il) MH 108 11.98%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 108 for stall controlled wind turbines Max thickness 11.9% at 22.8% chord Max camber 1% at 22.8% chord Max Cl/Cd 58.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx72ls160-il) FX 72-LS-160		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 72-LS-160 airfoil Max thickness 16% at 37.1% chord Max camber 8.2% at 43.5% chord Max Cl/Cd 58.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca4421-il) NACA 4421		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4421 airfoil Max thickness 21% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 58.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(bacxxx-il) BOEING BACXXX AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company BACXXX Energy Efficient Transport Program airfoil Max thickness 11.3% at 35% chord Max camber 1.4% at 15% chord Max Cl/Cd 58.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e1211-il) EPPLER 1211 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1211 general aviation airfoil Max thickness 18% at 20.9% chord Max camber 4.4% at 37.7% chord Max Cl/Cd 58.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(naca634221-il) NACA 63(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(4)-221 airfoil Max thickness 21% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 58.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(arad13-il) ARA-D 13% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 13% thick propeller airfoil Max thickness 13% at 25% chord Max camber 3.6% at 30% chord Max Cl/Cd 58.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e325-il) EPPLER 325 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E325 flying wing airfoil Max thickness 12.6% at 34.3% chord Max camber 1.8% at 16.3% chord Max Cl/Cd 58.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ag08-il) AG08		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG08 airfoil Max thickness 5.8% at 21% chord Max camber 1.7% at 40.4% chord Max Cl/Cd 58.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ag455ct02r-il) AG455ct -02f rot.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG455ct -02f airfoil Max thickness 6.5% at 23.3% chord Max camber 1.8% at 33.1% chord Max Cl/Cd 58.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database