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.

(glennmartin4-il) Glenn Martin 4		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Glenn Martin 4 airfoil Max thickness 15.5% at 30% chord Max camber 6% at 30% chord Max Cl/Cd 40.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(usa31-il) USA 31 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-31 airfoil Max thickness 14.8% at 19.7% chord Max camber 9.3% at 39.7% chord Max Cl/Cd 40.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(p51dtip-il) P-51D TIP (BL215) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	P-51D tip (BL215) airfoil Max thickness 11.4% at 46.3% chord Max camber 1.3% at 46.3% chord Max Cl/Cd 40.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe386-il) GOE 386 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 386 airfoil Max thickness 20.3% at 29% chord Max camber 5.4% at 39% chord Max Cl/Cd 40.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e550-il) EPPLER 550 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E550 general aviation airfoil Max thickness 18.2% at 34% chord Max camber 2.2% at 29.4% chord Max Cl/Cd 40.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe411-il) GOE 411 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 411 airfoil Max thickness 13.2% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 40.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(lwk80120k25-il) LWK 80-120/K25		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LWK 80-120/K25 symmetrical airfoil Max thickness 12.1% at 40.2% chord Max camber 0% at 0% chord Max Cl/Cd 40.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca1408-il) NACA 1408		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 1408 airfoil Max thickness 8% at 30% chord Max camber 1% at 40% chord Max Cl/Cd 40.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e332-il) EPPLER 332 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E332 flying wing airfoil Max thickness 11.5% at 32.3% chord Max camber 3.1% at 22.6% chord Max Cl/Cd 40.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca633018-il) NACA 63(3)-018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(3)-018 airfoil Max thickness 18% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 40.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database