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.

(n2414-il) NACA 2414		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2414 airfoil Max thickness 14% at 29.5% chord Max camber 2% at 39.6% chord Max Cl/Cd 32.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe55-il) GOE 55 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 55 airfoil Max thickness 6.2% at 14.9% chord Max camber 2% at 19.9% chord Max Cl/Cd 32.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(defcnd3-il) DEFIANT CANARD BL145 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan DEFIANT canard BL145 airfoil Max thickness 11.5% at 28.6% chord Max camber 2.4% at 28.6% chord Max Cl/Cd 32.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e68-il) EPPLER 68 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E68 low Reynolds number airfoil Max thickness 13.1% at 32% chord Max camber 3.3% at 50.9% chord Max Cl/Cd 32.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(usnps4-il) USNPS4 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Jacobs USNPS4 (smoothed) 17.5 kW wind turbine airfoil Max thickness 11.9% at 34.2% chord Max camber 5% at 34.2% chord Max Cl/Cd 32.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(s8055-il) S8055 (12%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8055 (12%) low Reynolds number airfoil Max thickness 12% at 33.9% chord Max camber 1.6% at 44.7% chord Max Cl/Cd 32.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(bambino6-il) Bambino 6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bambino 6 airfoil Max thickness 12% at 40% chord Max camber 2.8% at 40% chord Max Cl/Cd 32.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sd7003-il) SD7003-085-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7003 low Reynolds number airfoil Max thickness 8.5% at 24.4% chord Max camber 1.2% at 38.3% chord Max Cl/Cd 32.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(giiih-il) GIII BL207 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.3% at 39.9% chord Max camber 1.3% at 29.9% chord Max Cl/Cd 32.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ag36-il) AG36		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG36 airfoil Max thickness 8.2% at 27.9% chord Max camber 2.3% at 37% chord Max Cl/Cd 32.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database