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.

(goe481-il) GOE 481 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 481 airfoil Max thickness 13.4% at 9.6% chord Max camber 8.8% at 39.4% chord Max Cl/Cd 63.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca63209-il) NACA 63-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-209 airfoil Max thickness 9% at 35% chord Max camber 1.1% at 50% chord Max Cl/Cd 63.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(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 63.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca001264a08cli02-il) NACA 0012-64 a=0.8 c(li)=0.2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0012-64 a=0.8 c(li)=0.2 airfoil Max thickness 11% at 39.9% chord Max camber 1.8% at 29.9% chord Max Cl/Cd 63.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(giiii-il) GIII BL288 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 8.5% at 40% chord Max camber 1.3% at 25% chord Max Cl/Cd 63.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(gu255118-il) UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Glasgow GU 25-5(11)8 canard airfoil (Quickie Max thickness 20% at 40% chord Max camber 7.1% at 45% chord Max Cl/Cd 63.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx38153-il) FX 38-153 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 38-153 airfoil Max thickness 15.5% at 43.5% chord Max camber 2.1% at 80.4% chord Max Cl/Cd 63.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(rae5212-il) RAE(NPL) 5212 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE(NPL) 5212 transonic airfoil Max thickness 11.9% at 35.5% chord Max camber 1.8% at 69.1% chord Max Cl/Cd 63.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca0015-il) NACA 0015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0015 airfoil Max thickness 15% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 63.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca64210-il) NACA 64-210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-210 airfoil Max thickness 10% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 63.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database