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.

(goe585-il) GOE 585 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 585 airfoil Max thickness 8.2% at 20% chord Max camber 3.4% at 40% chord Max Cl/Cd 70.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx66s171-il) FX 66-S-171 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-S-171 airfoil Max thickness 17.1% at 33.9% chord Max camber 3.9% at 43.5% chord Max Cl/Cd 70.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e552-il) EPPLER 552 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E552 general aviation airfoil Max thickness 18.4% at 32.4% chord Max camber 2.6% at 51.8% chord Max Cl/Cd 70.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s7012-il) S7012 8.75%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S7012 low Reynolds number airfoil Max thickness 8.7% at 27.7% chord Max camber 1.7% at 38.1% chord Max Cl/Cd 70.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(psu-90-125wl-il) PSU-90-125WL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	PSU-90-125WL sailplane winglet airfoil Max thickness 12.5% at 35.1% chord Max camber 2% at 54.4% chord Max Cl/Cd 70.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(s3014-il) S3014-095-85		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3014 low Reynolds number airfoil Max thickness 9.5% at 29.4% chord Max camber 2.6% at 38.6% chord Max Cl/Cd 70.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sd7062-il) SD7062 (14%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7062 low Reynolds number airfoil Max thickness 14% at 25.5% chord Max camber 3.5% at 38.8% chord Max Cl/Cd 70.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh70-il) MH 70 11.08%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 70 for fying wing (full size) Max thickness 11.1% at 29.4% chord Max camber 3% at 39.6% chord Max Cl/Cd 70.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(raf6-il) RAF 6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-6 airfoil Max thickness 10% at 30% chord Max camber 4.6% at 30% chord Max Cl/Cd 70.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(m16-il) NACA M16 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-16 airfoil Max thickness 6.2% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 70.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database