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.

(goe398-il) GOE 398 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 398 airfoil Max thickness 13.9% at 30% chord Max camber 4.9% at 40% chord Max Cl/Cd 120.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(marske7-il) RONCZ LOW DRAG FLYING WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz/Marske-7 low drag flying wing airfoil Max thickness 12.1% at 42.8% chord Max camber 2.8% at 39.1% chord Max Cl/Cd 120.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(mh104-il) MH 104 15.28%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 104 for stall controlled wind turbines Max thickness 15.2% at 26.4% chord Max camber 1.9% at 31.1% chord Max Cl/Cd 120.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(davis-il) Davis AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Consolidated/Davis airfoil (B-24 wing?) Max thickness 11.3% at 30% chord Max camber 3.7% at 40% chord Max Cl/Cd 120.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca662415-il) NACA 66(2)-415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(2)-415 airfoil Max thickness 15% at 45% chord Max camber 2.2% at 50% chord Max Cl/Cd 120.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe137-il) GOE 137 (MVA H.15) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 137 (MVA H.15) airfoil Max thickness 8.6% at 29.9% chord Max camber 4.4% at 39.9% chord Max Cl/Cd 120.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe621-il) GOE 621 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 621 airfoil Max thickness 15% at 29.5% chord Max camber 5% at 49.5% chord Max Cl/Cd 120.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e580-il) EPPLER 580 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E580 general purpose airfoil Max thickness 16.1% at 33% chord Max camber 4.1% at 61.2% chord Max Cl/Cd 120.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ah93w257-il) AH 93-W-257		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-W-257 airfoil for use on wind turbines (W) Max thickness 25.7% at 30.9% chord Max camber 2.1% at 77.8% chord Max Cl/Cd 120.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e636-il) EPPLER 636 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E636 airfoil Max thickness 11.9% at 26.9% chord Max camber 3.2% at 22.9% chord Max Cl/Cd 120.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database