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.

(ah82150a-il) AH 82-150 A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 82-150 A airfoil Max thickness 15% at 40.2% chord Max camber 3.3% at 43.5% chord Max Cl/Cd 42.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(eh2012-il) EH 2.0/12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 2.0/12 for tailless R/C aircraft Max thickness 12% at 28.7% chord Max camber 2% at 25.9% chord Max Cl/Cd 42.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca25112-jf) NACA 25112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 25112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 2% at 27.2% chord Max Cl/Cd 42.5 at Re# 100,000 Source Javafoil generated
(goe625-il) GOE 625 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 625 airfoil Max thickness 20% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 42.4 at Re# 100,000 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 42.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(giiic-il) GIII BL75 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 9.9% at 39.8% chord Max camber 0.9% at 29.8% chord Max Cl/Cd 42.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e341-il) EPPLER 341 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E341 flying wing airfoil Max thickness 13.9% at 32.8% chord Max camber 3% at 23.2% chord Max Cl/Cd 42.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(b707c-il) BOEING 707 .40 SPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company model 707 airfoils Max thickness 9.6% at 30% chord Max camber 1.9% at 15% chord Max Cl/Cd 42.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx66s161-il) FX 66-S-161 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-S-161 airfoil Max thickness 16.1% at 33.9% chord Max camber 3.9% at 43.5% chord Max Cl/Cd 42.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe620-il) GOE 620 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 620 airfoil Max thickness 17.5% at 30% chord Max camber 5.9% at 50% chord Max Cl/Cd 42.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database