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.

(naca23021-il) NACA 23021		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23021 airfoil Max thickness 21% at 30% chord Max camber 1.9% at 10% chord Max Cl/Cd 18.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n66021-il) NACA 66-021 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(4)-021 airfoil Max thickness 21% at 45% chord Max camber 0% at 0% chord Max Cl/Cd 18.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ls421mod-il) NASA/LANGLEY LS(1)-0421MOD 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)-0421MOD general aviation airfoil Max thickness 21% at 32.5% chord Max camber 2.3% at 30% chord Max Cl/Cd 18.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e1214-il) EPPLER 1214 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1214 general aviation airfoil Max thickness 19.8% at 26.2% chord Max camber 2.1% at 30.4% chord Max Cl/Cd 18.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca643618-il) NACA 64(3)-618		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(3)-618 airfoil Max thickness 17.9% at 34.7% chord Max camber 3.3% at 50% chord Max Cl/Cd 18.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(n8h12-il) NACA 8-H-12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 8-H-12 rotorcraft airfoil Max thickness 12% at 30% chord Max camber 3.5% at 30% chord Max Cl/Cd 18.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n1h15-il) NACA 1-H-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 1-H-15 rotorcraft airfoil Max thickness 14.7% at 40% chord Max camber 5.5% at 40% chord Max Cl/Cd 18.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx63147-il) FX 63-147 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-147 airfoil Max thickness 14.7% at 33.9% chord Max camber 3.1% at 33.9% chord Max Cl/Cd 18.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe646-il) GOE 646 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 646 airfoil Max thickness 18.3% at 29% chord Max camber 4.5% at 49% chord Max Cl/Cd 18.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e544-il) EPPLER 544 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E544 general aviation airfoil Max thickness 17.5% at 40% chord Max camber 1.9% at 30.5% chord Max Cl/Cd 18.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database