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.

(lwk80080-il) LWK 80-080		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LWK 80-080 symmetrical airfoil Max thickness 8.1% at 40.2% chord Max camber 0% at 0% chord Max Cl/Cd 47.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(lwk80080-il) LWK 80-080		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LWK 80-080 symmetrical airfoil Max thickness 8.1% at 40.2% chord Max camber 0% at 0% chord Max Cl/Cd 47.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca001066-il) NACA 0010-66		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-66 airfoil Max thickness 10% at 60% chord Max camber 0% at 0% chord Max Cl/Cd 47.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe229-il) GOE 229 (MVA H.39) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 229 (MVA H.39) airfoil Max thickness 19.3% at 29% chord Max camber 5.9% at 49.1% chord Max Cl/Cd 47.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ea61012-il) EPPLER EA 6(-1)-012 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler EA 6(-1)-012 airfoil Max thickness 12% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 47.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(fx69pr281-il) FX 69-PR-281		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 69-PR-281 airfoil Max thickness 28.1% at 22.2% chord Max camber 5.6% at 50% chord Max Cl/Cd 47.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(r140-il) R140 (original)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	R140 Quickee 500 airfoil (original) Max thickness 12% at 39.3% chord Max camber 0.5% at 42.3% chord Max Cl/Cd 47.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(cp-180-050-gn) Cambered plate C=18% T=5% R=0.78		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	HAWT pipe blade with coordinates based on top surface. Camber=18% Wall thickness=5% Radius=0.784 Max thickness 5% at 3.2% chord Max camber 16.4% at 49.3% chord Max Cl/Cd 46.7 at Re# 500,000 Source Generated
(du861372-il) DU 86-137/25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Delft University DU 86-137/25 Airfoil Max thickness 13.6% at 41.6% chord Max camber 0.3% at 1.6% chord Max Cl/Cd 46.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n64008a-il) NACA 64-008A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-008A airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 46.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database