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.

(npl9660-il) NPL 9660 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9660 rotorcraft airfoil Max thickness 11.3% at 34.2% chord Max camber 1% at 19.8% chord Max Cl/Cd 66.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e228-il) E10(08%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E228 low Reynolds number airfoil Max thickness 10.1% at 31.9% chord Max camber 0.3% at 31.9% chord Max Cl/Cd 66.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(npl9627-il) NPL 9627 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9627 rotorcraft airfoil Max thickness 12.2% at 31% chord Max camber 0.9% at 40.4% chord Max Cl/Cd 66.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca0012h-sa) NACA0012H for VAWT from Sandia report SAND80-2114		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Modified Naca 0012 airfoil for Sandia VAWT tests Max thickness 12.2% at 22.5% chord Max camber 0% at 0% chord Max Cl/Cd 66.2 at Re# 500,000 Source Sandia National Laboratories
(dfvlrr4-il) DFVLR R-4 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	DFVLR R-4 transonic airfoil Max thickness 13.4% at 37.9% chord Max camber 2.1% at 79.9% chord Max Cl/Cd 66.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(s1048-il) S1048 14% (Danny Howell)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1048 airfoil Max thickness 14% at 27% chord Max camber 0% at 0% chord Max Cl/Cd 66.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe513-il) GOE 513 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 513 airfoil Max thickness 16.6% at 29.8% chord Max camber 5.2% at 39.8% chord Max Cl/Cd 66.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hq109-il) HQ 1.0/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.0/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 1% at 50% chord Max Cl/Cd 66.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca651212-il) NACA 65(1)-212		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(1)-212 airfoil Max thickness 12% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 66.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe531-il) GOE 531 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 531 airfoil Max thickness 13.8% at 19.5% chord Max camber 14.7% at 49.3% chord Max Cl/Cd 66.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database