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.

(goe376-il) GOE 376 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 376 airfoil Max thickness 6.6% at 30% chord Max camber 5% at 30% chord Max Cl/Cd 76.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe360-il) GOE 360 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 360 airfoil Max thickness 9.7% at 29.9% chord Max camber 5.9% at 29.9% chord Max Cl/Cd 76.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hor12-il) ONERA HOR12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Onera propeller blade airfoils from US Patent 4 Max thickness 11.9% at 22.8% chord Max camber 3.7% at 46.2% chord Max Cl/Cd 76.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(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 76.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx601261-il) WORTMANN FX 60-126/1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-126/1 airfoil Max thickness 12.6% at 27.9% chord Max camber 4% at 56.5% chord Max Cl/Cd 76.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe692-il) GOE 692 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 692 airfoil Max thickness 16.1% at 30% chord Max camber 5% at 40% chord Max Cl/Cd 76.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s3024-il) AIRFOIL 3024 9.84%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3024 low Reynolds number airfoil Max thickness 9.8% at 30.7% chord Max camber 3% at 44.7% chord Max Cl/Cd 76.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s806a-nr) NREL's S806A Airfoil (modified line 35)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S806A tip Max thickness 11.5% at 45% chord Max camber 2.8% at 45% chord Max Cl/Cd 76.1 at Re# 200,000 Source NWTC National WInd Technology Center
(e580-il) EPPLER 580 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E580 general purpose airfoil Max thickness 16.1% at 33% chord Max camber 4.1% at 61.2% chord Max Cl/Cd 76.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh200-il) MH 200 12.97%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 200 for a canard airplane (main wing) Max thickness 13% at 39.5% chord Max camber 2.1% at 49.8% chord Max Cl/Cd 76.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database