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.

(dae31-il) DAE-31 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela DAE31 low Reynolds number airfoil Max thickness 11.1% at 29.3% chord Max camber 6.7% at 47% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca642415-il) NACA 64(2)-415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(2)-415 airfoil Max thickness 15% at 34.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh108-il) MH 108 11.98%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 108 for stall controlled wind turbines Max thickness 11.9% at 22.8% chord Max camber 1% at 22.8% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(atr72sm-il) Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ATR 72 wing airfoil (from NTSB report) Max thickness 14.5% at 25.4% chord Max camber 2.9% at 21.4% chord Max Cl/Cd 25.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe562-il) GOE 562 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 562 airfoil Max thickness 14.1% at 30% chord Max camber 6.3% at 30% chord Max Cl/Cd 25.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(ah93k132-il) AH 93-K-132/15		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-K-132/15 airfoil for use with flaps (K) Max thickness 13.2% at 41.2% chord Max camber 3.5% at 41.2% chord Max Cl/Cd 25.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca001064-il) NACA 0010-64		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-64 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 25.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(oa209-il) ONERA OA209 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OA209 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 9% at 29.3% chord Max camber 1.6% at 17.1% chord Max Cl/Cd 25.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx84w127-il) FX 84-W-127		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 84-W-127 airfoil for use on wind turbines (W) Max thickness 12.8% at 33.9% chord Max camber 3.7% at 40.2% chord Max Cl/Cd 25.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca001264-il) NACA 0012-64		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0012-64 airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 25.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database