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.

(ah83159-il) AH 83-159		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 83-159 airfoil Max thickness 15.9% at 40.2% chord Max camber 3.8% at 40.2% chord Max Cl/Cd 136.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(r1082-il) RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1082 Voyager root outer aft wing airfoil Max thickness 18% at 40% chord Max camber 3.4% at 40% chord Max Cl/Cd 136.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe484-il) GOE 484 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 484 airfoil Max thickness 6.3% at 30% chord Max camber 5% at 50% chord Max Cl/Cd 136.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(spicasm-il) SPICA 11.73% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Anderson SPICA R/C sailplane airfoil (smoothed) Max thickness 11.7% at 30% chord Max camber 4.7% at 35% chord Max Cl/Cd 136.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e715-il) EPPLER 715 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E715 tailplane airfoil Max thickness 15% at 33.1% chord Max camber 2.8% at 42% chord Max Cl/Cd 136.7 at Re# 1,000,000 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 136.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca6412-il) NACA 6412		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6412 airfoil Max thickness 12% at 30.1% chord Max camber 6% at 39.6% chord Max Cl/Cd 136.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe723-il) GOE 723 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 723 airfoil Max thickness 11.6% at 29.7% chord Max camber 4.5% at 49.7% chord Max Cl/Cd 136.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e68-il) EPPLER 68 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E68 low Reynolds number airfoil Max thickness 13.1% at 32% chord Max camber 3.3% at 50.9% chord Max Cl/Cd 136.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe265-il) GOE 265 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 265 airfoil Max thickness 7.7% at 14.9% chord Max camber 7.3% at 39.9% chord Max Cl/Cd 136.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database