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.

(m9-il) NACA M9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-9 airfoil Max thickness 10.4% at 15% chord Max camber 7.2% at 30% chord Max Cl/Cd 99.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe619-il) GOE 619 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 619 airfoil Max thickness 13.7% at 19.5% chord Max camber 4.5% at 49.5% chord Max Cl/Cd 99.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s8036-il) S8036 (16%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8036 low Reynolds number airfoil Max thickness 16% at 36.8% chord Max camber 1.3% at 40.4% chord Max Cl/Cd 99.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe600-il) GOE 600 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 600 airfoil Max thickness 13.1% at 29.4% chord Max camber 1.9% at 49.4% chord Max Cl/Cd 99.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(m9-il) NACA M9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-9 airfoil Max thickness 10.4% at 15% chord Max camber 7.2% at 30% chord Max Cl/Cd 99.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(s811-nr) NREL's S811 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S811 root Max thickness 26.3% at 27.4% chord Max camber 1.7% at 76.4% chord Max Cl/Cd 99.5 at Re# 1,000,000 Source NWTC National WInd Technology Center
(hq3514-il) HQ 3.5/14 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/14 R/C sailplane airfoil Max thickness 14% at 35% chord Max camber 3.5% at 50% chord Max Cl/Cd 99.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe510-il) GOE 510 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 510 airfoil Max thickness 13.7% at 19.7% chord Max camber 5.8% at 39.7% chord Max Cl/Cd 99.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe240-il) GOE 240 (KOLLER) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 240 (KOLLER) airfoil Max thickness 7% at 29.9% chord Max camber 5.2% at 39.9% chord Max Cl/Cd 99.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe610b-il) GOE 610 B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 610 B airfoil Max thickness 7.8% at 39.9% chord Max camber 5.3% at 39.9% chord Max Cl/Cd 99.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database