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.

(sc21006-il) NASA SC(2)-1006 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-1006 airfoil Max thickness 6% at 30% chord Max camber 2.6% at 73% chord Max Cl/Cd 48.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n5h10-il) NACA 5-H-10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 5-H-10 rotorcraft airfoil Max thickness 9.9% at 40% chord Max camber 2.3% at 40% chord Max Cl/Cd 48.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rg12-il) RG-12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 12 airfoil Max thickness 9.3% at 34.4% chord Max camber 1.4% at 34.4% chord Max Cl/Cd 48.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(usa51-il) USA 51 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-51 airfoil Max thickness 9.3% at 30% chord Max camber 2.6% at 30% chord Max Cl/Cd 48.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(m6-il) NACA M6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-6 airfoil Max thickness 12% at 30% chord Max camber 2.2% at 30% chord Max Cl/Cd 48.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(ls413-il) NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0413 (GA(W)-2) general aviation airfoil Max thickness 12.9% at 37.5% chord Max camber 2.4% at 65% chord Max Cl/Cd 48.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe676-il) GOE 676 (= M 12) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 676 (= M 12) airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord Max Cl/Cd 48.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(m6-il) NACA M6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-6 airfoil Max thickness 12% at 30% chord Max camber 2.2% at 30% chord Max Cl/Cd 48.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(nacam12-il) NACA M12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA M12 airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord Max Cl/Cd 48.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe512-il) GOE 512 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 512 airfoil Max thickness 13.9% at 19.9% chord Max camber 5.6% at 29.9% chord Max Cl/Cd 48.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database