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.

(goe437-il) GOE 437 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 437 airfoil Max thickness 7.1% at 30% chord Max camber 4.8% at 40% chord Max Cl/Cd 78.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(m26-il) NACA M26 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-26 airfoil Max thickness 8.3% at 40% chord Max camber 8.3% at 30% chord Max Cl/Cd 78.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s4180-il) S4180-098-84		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4180 low Reynolds number airfoil Max thickness 9.8% at 26.1% chord Max camber 4% at 39.4% chord Max Cl/Cd 78.7 at Re# 200,000 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 78.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe226-il) GOE 226 (MVA H.36) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 226 (MVA H.36) airfoil Max thickness 13.9% at 19.7% chord Max camber 8.1% at 49.7% chord Max Cl/Cd 78.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe682-il) GOE 682 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 682 airfoil Max thickness 10.7% at 30% chord Max camber 4.3% at 40% chord Max Cl/Cd 78.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(m20-il) NACA M20 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-20 airfoil Max thickness 8.2% at 30% chord Max camber 6.1% at 30% chord Max Cl/Cd 78.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e585-il) EPPLER 585 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E585 sailplane airfoil Max thickness 14.6% at 37.6% chord Max camber 4.2% at 42.8% chord Max Cl/Cd 78.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe492-il) GOE 492 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 492 airfoil Max thickness 6.2% at 29.9% chord Max camber 3.4% at 49.9% chord Max Cl/Cd 78.6 at Re# 200,000 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 78.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database