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.

(s4310-il) S4310		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4310 low Reynolds number airfoil Max thickness 10.9% at 30.7% chord Max camber 4.2% at 39.8% chord Max Cl/Cd 56.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sd7032-il) SD7032-099-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7032 low Reynolds number airfoil Max thickness 10% at 26.6% chord Max camber 3.4% at 45.1% chord Max Cl/Cd 56.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e178-il) E178 (8.69%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E178 low Reynolds number airfoil Max thickness 8.7% at 29.8% chord Max camber 2.8% at 38.8% chord Max Cl/Cd 56.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sd2030-il) SD2030-086-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD2030 low Reynolds number airfoil Max thickness 8.6% at 35.5% chord Max camber 2.2% at 45.3% chord Max Cl/Cd 56.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(usa5-il) USA 5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-5 airfoil Max thickness 6.4% at 30% chord Max camber 4.5% at 40% chord Max Cl/Cd 56.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe550-il) GOE 550 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 550 airfoil Max thickness 13% at 20% chord Max camber 4.3% at 50% chord Max Cl/Cd 56.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(clarkv-il) CLARK V AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK V airfoil Max thickness 11.6% at 30% chord Max camber 3.4% at 50% chord Max Cl/Cd 56.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e195-il) E195 (11.82%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E195 low Reynolds number airfoil Max thickness 11.8% at 35% chord Max camber 2.7% at 44.2% chord Max Cl/Cd 56.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(raf32-il) RAF 32 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-32 airfoil Max thickness 12.7% at 30% chord Max camber 5% at 50% chord Max Cl/Cd 56.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n11-il) N-11		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-11 airfoil Max thickness 10.9% at 30% chord Max camber 4.4% at 40% chord Max Cl/Cd 56.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database