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.

(naca001035-il) NACA 0010-35		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-35 airfoil Max thickness 10% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 24 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s812-nr) NREL's S812 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S812 primary Max thickness 21% at 39.6% chord Max camber 1.6% at 77% chord Max Cl/Cd 23.9 at Re# 100,000 Source NWTC National WInd Technology Center
(ah95160-il) AH 95-160		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 95-160 airfoil Max thickness 16% at 38.9% chord Max camber 5.6% at 44.6% chord Max Cl/Cd 23.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(b737a-il) BOEING 737 ROOT AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company model 737 airfoils Max thickness 15.4% at 19.6% chord Max camber 0.2% at 5% chord Max Cl/Cd 23.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ua2-180-il) UA(2)-180 (University of Alberta/Marsden)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	UA(2)-180 airfoil for ultralight category aircraft Max thickness 18.1% at 31.5% chord Max camber 7% at 36.6% chord Max Cl/Cd 23.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe09k-il) GOE 9K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 9K airfoil Max thickness 2.5% at 50% chord Max camber 0.9% at 60% chord Max Cl/Cd 23.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe09k-il) GOE 9K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 9K airfoil Max thickness 2.5% at 50% chord Max camber 0.9% at 60% chord Max Cl/Cd 23.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n66021-il) NACA 66-021 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(4)-021 airfoil Max thickness 21% at 45% chord Max camber 0% at 0% chord Max Cl/Cd 23.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe16k-il) GOE 16K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 16K airfoil Max thickness 18.2% at 50% chord Max camber 4.1% at 50% chord Max Cl/Cd 23.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ua2-180sm-il) UA(2)-180 smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	UA(2)-180 (smoothed) airfoil for ultralight category aircraft Max thickness 18.2% at 34.1% chord Max camber 6.5% at 39.3% chord Max Cl/Cd 23.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database