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.

(e639-il) EPPLER 639 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E639 airfoil Max thickness 12.6% at 29.2% chord Max camber 4.8% at 29.2% chord Max Cl/Cd 102.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe553-il) GOE 553 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 553 airfoil Max thickness 13.7% at 29.6% chord Max camber 4.7% at 39.6% chord Max Cl/Cd 102.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sg6051-il) SG6051		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Giguere SG6051 wind turbine airfoil Max thickness 12% at 35.7% chord Max camber 3.1% at 49.9% chord Max Cl/Cd 102.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(m25-il) NACA M25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-25 airfoil Max thickness 6.3% at 30% chord Max camber 8.2% at 30% chord Max Cl/Cd 102.3 at Re# 500,000 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 102.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(hs1404-il) HAM-STD HS1-404 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	HS1 family of prop airfoils from US Patent No. 4 Max thickness 4% at 18% chord Max camber 3.1% at 46% chord Max Cl/Cd 102.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n1h15-il) NACA 1-H-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 1-H-15 rotorcraft airfoil Max thickness 14.7% at 40% chord Max camber 5.5% at 40% chord Max Cl/Cd 102.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(r1080-il) RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1080 Voyager inner aft wing airfoil Max thickness 18% at 40% chord Max camber 3.3% at 40% chord Max Cl/Cd 102.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe602-il) GOE 602 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 602 airfoil Max thickness 10% at 30% chord Max camber 3.5% at 40% chord Max Cl/Cd 102.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe79-il) GOE 79 (PFALZ 11) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 79 (Pfalz 11) airfoil Max thickness 6.2% at 14.9% chord Max camber 6% at 29.9% chord Max Cl/Cd 102.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database