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.

(goe775-il) GOE 775 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 775 airfoil Max thickness 21% at 30% chord Max camber 0% at 1.3% chord Max Cl/Cd 36.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq09-il) HQ 0/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 0/9 R/C sailplane airfoil Max thickness 8.1% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 36.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca22112-jf) NACA 22112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 22112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 0.8% at 9.6% chord Max Cl/Cd 36.8 at Re# 100,000 Source Javafoil generated
(naca2424-il) NACA 2424		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2424 airfoil Max thickness 24% at 29.7% chord Max camber 2% at 40% chord Max Cl/Cd 36.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n64015a-il) NACA 642-015A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(2)-015A airfoil Max thickness 15% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 36.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(s833-nr) NREL's S833 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S833 primary 18.0% Dia=1 to 3 m Re=4.0E+5 Clmax(S)=1.10 Clmax(R)=1.13 High max lift coef Max thickness 18% at 36.3% chord Max camber 2.5% at 78.8% chord Max Cl/Cd 36.8 at Re# 100,000 Source NWTC National WInd Technology Center
(n14-il) N-14		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-14 airfoil Max thickness 11.5% at 30% chord Max camber 0.1% at 20% chord Max Cl/Cd 36.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca001234-il) NACA 0012-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0012-34 airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 36.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca66210-il) NACA 66-210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66-210 airfoil Max thickness 10% at 45% chord Max camber 1.1% at 50% chord Max Cl/Cd 36.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe434-il) GOE 434 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 434 airfoil Max thickness 22.8% at 28.4% chord Max camber 5.2% at 48.5% chord Max Cl/Cd 36.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database