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.

(sc20414-il) NASA SC(2)-0414 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0414 airfoil (NASA TP-2969) Max thickness 14% at 36% chord Max camber 1.5% at 83% chord Max Cl/Cd 35.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sc20404-il) NASA SC(2)-0404 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0404 airfoil (NASA TP-2969) Max thickness 4% at 37% chord Max camber 0.7% at 81% chord Max Cl/Cd 35.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sc20404-il) NASA SC(2)-0404 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0404 airfoil (NASA TP-2969) Max thickness 4% at 37% chord Max camber 0.7% at 81% chord Max Cl/Cd 35.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe444-il) GOE 444 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 444 airfoil Max thickness 5.6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 35.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ht12-il) HT12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT12 airfoil Max thickness 5% at 18.6% chord Max camber 0% at 0% chord Max Cl/Cd 35.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(sc20412-il) NASA SC(2)-0412 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0412 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 1.3% at 83% chord Max Cl/Cd 35.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe776-il) GOE 776 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 776 airfoil Max thickness 25% at 30% chord Max camber 0% at 60% chord Max Cl/Cd 35.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(k2-il) GRUMMAN K-2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman K-2 transonic airfoil (GAC .80-.53-10.3) Max thickness 10.3% at 38.9% chord Max camber 1.3% at 88.3% chord Max Cl/Cd 35.1 at Re# 200,000 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 35 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s827-nr) NREL's S827 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S827 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.00 Clmax(R)=0.99 Restrained max lift coef Max thickness 21% at 44.9% chord Max camber 2.2% at 68% chord Max Cl/Cd 35 at Re# 200,000 Source NWTC National WInd Technology Center