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.

(s7012-il) S7012 8.75%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S7012 low Reynolds number airfoil Max thickness 8.7% at 27.7% chord Max camber 1.7% at 38.1% chord Max Cl/Cd 67.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe375-il) GOE 375 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 375 airfoil Max thickness 6.5% at 20% chord Max camber 4.5% at 30% chord Max Cl/Cd 67.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(amsoil1-il) RUTAN CANARD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan AMSOIL racer canard airfoil Max thickness 11.6% at 39% chord Max camber 2.1% at 42% chord Max Cl/Cd 67.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe795-il) GOE 795 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 795 airfoil Max thickness 8% at 30.9% chord Max camber 2.4% at 43.5% chord Max Cl/Cd 67.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca2411-il) NACA 2.5411		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2411 airfoil Max thickness 11% at 29.5% chord Max camber 2.5% at 39.6% chord Max Cl/Cd 67.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe507-il) GOE 507 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 507 airfoil Max thickness 8.7% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 67.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah81k144-il) AH 81-K-144/17		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 81-K-144/17 airfoil for use with flaps (K) Max thickness 14.5% at 40.2% chord Max camber 4.2% at 46.7% chord Max Cl/Cd 67.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe633-il) GOE 633 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 633 airfoil Max thickness 13.8% at 19.7% chord Max camber 4% at 39.7% chord Max Cl/Cd 67.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe534-il) GOE 534 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 534 airfoil Max thickness 14.1% at 19.6% chord Max camber 5.2% at 39.6% chord Max Cl/Cd 67.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx6617a2-il) FX 66-17AII-182 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-17AII-182 airfoil Max thickness 18.2% at 33.9% chord Max camber 3.8% at 37.1% chord Max Cl/Cd 67.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database