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.

(goe11k-il) GOE 11K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 11K airfoil Max thickness 7.5% at 50% chord Max camber 2.7% at 60% chord Max Cl/Cd 72.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx66s171-il) FX 66-S-171 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-S-171 airfoil Max thickness 17.1% at 33.9% chord Max camber 3.9% at 43.5% chord Max Cl/Cd 72.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e551-il) EPPLER 551 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E551 general aviation airfoil Max thickness 18.2% at 32.4% chord Max camber 2.8% at 57.1% chord Max Cl/Cd 72.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe464-il) GOE 464 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 464 airfoil Max thickness 7.7% at 7.4% chord Max camber 9.9% at 29.9% chord Max Cl/Cd 72.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx63158-il) FX 63-158 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-158 airfoil Max thickness 15.8% at 33.9% chord Max camber 3.8% at 37.1% chord Max Cl/Cd 72.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(usa5-il) USA 5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-5 airfoil Max thickness 6.4% at 30% chord Max camber 4.5% at 40% chord Max Cl/Cd 72.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe15-il) GOE 15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 15 airfoil Max thickness 9% at 29.8% chord Max camber 7.8% at 29.8% chord Max Cl/Cd 72.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(vr7-il) BOEING-VERTOL VR-7 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-7 rotorcraft airfoil Max thickness 12% at 33% chord Max camber 3.1% at 33% chord Max Cl/Cd 72.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(clarkx-il) CLARK X AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK X airfoil Max thickness 11.7% at 30% chord Max camber 3.3% at 40% chord Max Cl/Cd 72.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(nacam18-il) NACA M18		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA M18 airfoil Max thickness 12% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 72.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database