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.

(e378-il) EPPLER 378 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E378 ultralight airfoil Max thickness 4.1% at 7.8% chord Max camber 8.1% at 35.9% chord Max Cl/Cd 36.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx67k170-il) FX 67-K-170/17 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 67-K-170/17 airfoil Max thickness 17% at 40.2% chord Max camber 5.1% at 43.5% chord Max Cl/Cd 36.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(nasasc2-0714-il) SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0714 airfoil (Ref. NASA TP-2890) Max thickness 13.9% at 37% chord Max camber 2.5% at 80% chord Max Cl/Cd 36.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx77w258-il) WORTMANN FX 77-W-258 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 77-W-258 wind turbine airfoil Max thickness 26.1% at 30.9% chord Max camber 4.3% at 27.9% chord Max Cl/Cd 36.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sc20518-il) NASA SC(2)-0518 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0518 airfoil (NASA TP-2969) Max thickness 18% at 35% chord Max camber 1.9% at 82% chord Max Cl/Cd 36.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(fx71089a-il) WORTMANN FX 71-089A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 71-089A airfoil Max thickness 8.9% at 22.2% chord Max camber 0% at 0% chord Max Cl/Cd 36.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(raf30md-il) RAF 30 MOD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-30 MOD airfoil Max thickness 7.6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 36.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(bambino6-il) Bambino 6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bambino 6 airfoil Max thickness 12% at 40% chord Max camber 2.8% at 40% chord Max Cl/Cd 36.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe388-il) GOE 388 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 388 airfoil Max thickness 10.2% at 29.9% chord Max camber 5.4% at 39.9% chord Max Cl/Cd 36.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(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 36.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database