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.

(goe405-il) GOE 405 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 405 airfoil Max thickness 11.1% at 30% chord Max camber 6.5% at 40% chord Max Cl/Cd 9.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(cap21c-il) CAP 21 (TraCFoil)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CAP 21 (TraCFoil) airfoil Max thickness 15.6% at 15.7% chord Max camber 0.6% at 23.9% chord Max Cl/Cd 9.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(wb140-il) WB-140/35/FB 14%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Woody Blanchard WB140/35/FB R/C sailplane airfoil Max thickness 13.9% at 30% chord Max camber 3.7% at 45% chord Max Cl/Cd 9.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh78-il) MH 78 14.47%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 78 for flying wings (hang glider) Max thickness 14.4% at 22.1% chord Max camber 1.9% at 17.9% chord Max Cl/Cd 9.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e598-il) EPPLER 598 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E598 airfoil Max thickness 11.1% at 24.2% chord Max camber 4.5% at 34.4% chord Max Cl/Cd 9.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(goe522-il) GOE 522 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 522 airfoil Max thickness 21.8% at 28.6% chord Max camber 5.2% at 48.7% chord Max Cl/Cd 9.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(lnv109a-il) LNV109A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Douglas/Liebeck LNV109A high lift airfoil Max thickness 13% at 23.5% chord Max camber 6% at 31.5% chord Max Cl/Cd 9.8 at Re# 50,000 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 9.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e210-il) E210 (13.64%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E210 low Reynolds number airfoil Max thickness 13.6% at 32.1% chord Max camber 3.7% at 50.7% chord Max Cl/Cd 9.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe238-il) GOE 238 (HANSA-BRANDENBURG) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 238 (HANSA-BRANDENBURG) airfoil Max thickness 9.8% at 29.8% chord Max camber 5.5% at 29.8% chord Max Cl/Cd 9.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database