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.

(goe410-il) GOE 410 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 410 airfoil Max thickness 16.1% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 25.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh91-il) MH 91 14.98%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 91 parafoil Max thickness 15% at 27.3% chord Max camber 1.4% at 18.7% chord Max Cl/Cd 25.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe679-il) GOE 679 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 679 airfoil Max thickness 18.3% at 29.1% chord Max camber 4.5% at 39.1% chord Max Cl/Cd 25.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe775-il) GOE 775 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 775 airfoil Max thickness 21% at 30% chord Max camber 0% at 1.3% chord Max Cl/Cd 25.1 at Re# 50,000 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 25.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(e682-il) EPPLER 682 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E682 sailplane airfoil Max thickness 15.3% at 40.4% chord Max camber 2.9% at 40.4% chord Max Cl/Cd 25.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca001034-il) NACA 0010-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-34 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 25.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(usa40b-il) USA 40 B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-40B airfoil Max thickness 13.6% at 20% chord Max camber 4% at 40% chord Max Cl/Cd 25.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ah93k130-il) AH 93-K-130/15		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-K-130/15 airfoil for use with flaps (K) Max thickness 13.1% at 42% chord Max camber 3.5% at 42% chord Max Cl/Cd 25.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(marske3-il) MARSKE PIONEER IID ROOT AIRFOIL (NACA 431012A/24112 HYBRID)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marske Pioneer IID root airfoil (NACA 43012A/24112 hybrid) Max thickness 12.1% at 30% chord Max camber 2.8% at 15% chord Max Cl/Cd 25 at Re# 50,000 Source UIUC Airfoil Coordinates Database