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.

(goe288-il) GOE 288 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 288 airfoil Max thickness 17.4% at 29.3% chord Max camber 5.5% at 39.3% chord Max Cl/Cd 27.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca2415-il) NACA 2415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2415 airfoil Max thickness 15% at 30% chord Max camber 2% at 40% chord Max Cl/Cd 27.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx711525-il) FX 71-L-150/25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 71-L-150/25 airfoil Max thickness 15% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 27.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh106-il) MH 106 13.07%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 106 for stall controlled wind turbines Max thickness 13.1% at 27.4% chord Max camber 0.9% at 27.4% chord Max Cl/Cd 27.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(lwk80120k25-il) LWK 80-120/K25		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LWK 80-120/K25 symmetrical airfoil Max thickness 12.1% at 40.2% chord Max camber 0% at 0% chord Max Cl/Cd 27.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(naca2418-il) NACA 2418		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2418 airfoil Max thickness 18% at 30% chord Max camber 2% at 40% chord Max Cl/Cd 27.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(m3-il) NACA M3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-3 airfoil Max thickness 11.9% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 27.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(nacam3-il) NACA M3		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA M3 airfoil Max thickness 11.9% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 27.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca23112-jf) NACA 23112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 23112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 1.2% at 14.7% chord Max Cl/Cd 27.3 at Re# 50,000 Source Javafoil generated
(oa206-il) ONERA OA206 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OA206 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 6% at 31.8% chord Max camber 0.8% at 19.6% chord Max Cl/Cd 27.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database