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.

(clarkyh-il) CLARK YH AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK YH airfoil Max thickness 11.9% at 30% chord Max camber 2.5% at 30% chord Max Cl/Cd 89.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ag45ct02r-il) AG45ct -02f		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG45ct -02f airfoil Max thickness 6.9% at 23.3% chord Max camber 1.8% at 33.1% chord Max Cl/Cd 89.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e426-il) EPPLER 426 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E426 airfoil Max thickness 10.8% at 25.5% chord Max camber 0.6% at 50.6% chord Max Cl/Cd 89 at Re# 1,000,000 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 89 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(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 89 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe344-il) GOE 344 (PFALZ 71) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 344 (Pfalz 71) airfoil Max thickness 7.2% at 19.9% chord Max camber 2.7% at 39.9% chord Max Cl/Cd 89 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(boe103-il) BOEING 103 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing 103 airfoil Max thickness 12.7% at 30% chord Max camber 3.6% at 40% chord Max Cl/Cd 89 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(mh93-il) MH 93 15.98%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 93 parafoil Max thickness 16% at 27.6% chord Max camber 1.4% at 15.2% chord Max Cl/Cd 88.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(usa28-il) USA 28 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-28 airfoil Max thickness 13.2% at 29.9% chord Max camber 3.8% at 49.9% chord Max Cl/Cd 88.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(mh110-il) MH 110 10.01%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 110 for stall controlled wind turbines (tip) Max thickness 10% at 23.9% chord Max camber 1% at 15.8% chord Max Cl/Cd 88.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database