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.

(n63215-il) NACA 63-215 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 98.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca65410-il) NACA 65-410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-410 airfoil Max thickness 10% at 39.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 98.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe390-il) GOE 390 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 390 airfoil Max thickness 20.3% at 29.2% chord Max camber 6.9% at 39.2% chord Max Cl/Cd 98.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sd7084-il) SD7084 (9.6%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7084 low Reynolds number airfoil Max thickness 9.6% at 29.5% chord Max camber 2.3% at 38.9% chord Max Cl/Cd 98.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe493-il) GOE 493 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 493 airfoil Max thickness 14.9% at 29.3% chord Max camber 3.4% at 49.3% chord Max Cl/Cd 98.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe422-il) GOE 422 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 422 airfoil Max thickness 17.1% at 29.5% chord Max camber 6.5% at 39.5% chord Max Cl/Cd 98.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(m12-il) NACA M12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-12 airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord Max Cl/Cd 98.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sd7080-il) SD7080 (9.2%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7080 low Reynolds number airfoil Max thickness 9.2% at 30% chord Max camber 2.1% at 44.4% chord Max Cl/Cd 98.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe244-il) GOE 244 (MVA PR.4) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 244 (MVA PR.4) airfoil Max thickness 17.7% at 19.6% chord Max camber 10% at 49.6% chord Max Cl/Cd 98.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe280-il) GOE 280 (DAIMLER XI) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 280 (DAIMLER XI) airfoil Max thickness 7.9% at 30% chord Max camber 4.5% at 30% chord Max Cl/Cd 98.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database