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.

(s3016-il) S3016-095-87		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3016 low Reynolds number airfoil Max thickness 9.5% at 28.9% chord Max camber 1.8% at 43.1% chord Max Cl/Cd 61 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ag45c03-il) AG45c -03f		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG45c -03f airfoil Max thickness 6.9% at 23.5% chord Max camber 2% at 31.7% chord Max Cl/Cd 61 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(rc12n1-il) NASA/LANGLEY RC-12(N)1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-12(N)1 rotorcraft airfoil Max thickness 12% at 37.4% chord Max camber 1.4% at 30% chord Max Cl/Cd 61 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(coanda1-il) Coanda 1		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Coanda 1 airfoil Max thickness 5.7% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 60.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hh02-il) HUGHES HELICOPTERS HH-02 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hughes helicopters HH-02 rotorcraft airfoil Max thickness 9.6% at 30% chord Max camber 2% at 40% chord Max Cl/Cd 60.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe114-il) GOE 114 (MVA MK.1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 114 (MVA MK.1) airfoil Max thickness 9.6% at 29.7% chord Max camber 3.5% at 49.7% chord Max Cl/Cd 60.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe512-il) GOE 512 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 512 airfoil Max thickness 13.9% at 19.9% chord Max camber 5.6% at 29.9% chord Max Cl/Cd 60.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e1230-il) EPPLER 1230 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1230 general aviation airfoil (Long-EZ and Defiant wing airfoil) Max thickness 17.4% at 30.9% chord Max camber 3.6% at 25.6% chord Max Cl/Cd 60.9 at Re# 200,000 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 60.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e326-il) EPPLER 326 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E326 flying wing airfoil Max thickness 12.9% at 33.4% chord Max camber 2.1% at 19.5% chord Max Cl/Cd 60.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database