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.

(goe226-il) GOE 226 (MVA H.36) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 226 (MVA H.36) airfoil Max thickness 13.9% at 19.7% chord Max camber 8.1% at 49.7% chord Max Cl/Cd 85.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe501-il) GOE 501 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 501 airfoil Max thickness 12.8% at 30% chord Max camber 6.3% at 50% chord Max Cl/Cd 85.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(la203a-il) DOUGLAS LA203A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Douglas/Liebeck LA203A high lift airfoil Max thickness 15.7% at 34.3% chord Max camber 5.5% at 46% chord Max Cl/Cd 85.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s801-nr) NREL's S801 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S801 primary 13.5% Not recommended Max thickness 13.5% at 37.8% chord Max camber 3.7% at 47.1% chord Max Cl/Cd 85.2 at Re# 200,000 Source NWTC National WInd Technology Center
(fx60100sm-il) FX60-100 10.0% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-100 airfoil (smoothed) Max thickness 10% at 27.9% chord Max camber 3.5% at 56.5% chord Max Cl/Cd 85.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(fx63137-il) WORTMANN FX 63-137 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-137 human power aircraft airfoil (Liver Puffin) airfoil Max thickness 13.7% at 30.9% chord Max camber 6% at 53.3% chord Max Cl/Cd 85.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh38-il) MH 38 9.68%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 38 for Endurance Model Max thickness 9.7% at 31.6% chord Max camber 3.9% at 45.3% chord Max Cl/Cd 85.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe123-il) GOE 123 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 123 airfoil Max thickness 5.4% at 25% chord Max camber 5.7% at 40% chord Max Cl/Cd 85 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe497-il) GOE 497 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 497 airfoil Max thickness 12.7% at 30% chord Max camber 5.3% at 50% chord Max Cl/Cd 85 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx60100-il) FX 60-100 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-100 airfoil Max thickness 10% at 27.9% chord Max camber 3.6% at 56.5% chord Max Cl/Cd 84.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database