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.

(nlf415-il) NASA/LANGLEY NLF(2)-0415 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley-DFVLR/Somers(NASA)-Horstmann(DFVLR) NLF(2)-0415 natural laminar flow airfoil Max thickness 15% at 47.1% chord Max camber 3% at 71.4% chord Max Cl/Cd 82.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e543-il) EPPLER 543 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E543 general aviation airfoil Max thickness 17.2% at 40.7% chord Max camber 1.9% at 31% chord Max Cl/Cd 82.7 at Re# 500,000 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 82.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fauvel-il) FAUVEL 14% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Fauvel 14% flying wing airfoil Max thickness 14% at 25.2% chord Max camber 2.5% at 25.2% chord Max Cl/Cd 82.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e546-il) EPPLER 546 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E546 general aviation airfoil Max thickness 16.2% at 40.3% chord Max camber 1.8% at 26.2% chord Max Cl/Cd 82.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(s3014-il) S3014-095-85		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3014 low Reynolds number airfoil Max thickness 9.5% at 29.4% chord Max camber 2.6% at 38.6% chord Max Cl/Cd 82.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s5020-il) S5020		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S5020 low Reynolds number airfoil Max thickness 8.4% at 27.8% chord Max camber 2.2% at 27.8% chord Max Cl/Cd 82.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e540-il) EPPLER 540 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E540 general aviation airfoil Max thickness 16.9% at 45.5% chord Max camber 1.6% at 35.7% chord Max Cl/Cd 82.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe620-il) GOE 620 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 620 airfoil Max thickness 17.5% at 30% chord Max camber 5.9% at 50% chord Max Cl/Cd 82.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca652215-il) NACA 65(2)-215		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(2)-215 airfoil Max thickness 15% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 82.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database