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.

(l188root-il) LOCKHEED L-188 ROOT AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed L-188/P-3 root airfoil NACA 0014 -1.10 40/1.051 Cli=.3 a=.8 Max thickness 14% at 41.3% chord Max camber 2% at 51.7% chord Max Cl/Cd 72.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe441-il) GOE 441 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 441 airfoil Max thickness 16% at 29.5% chord Max camber 7.7% at 39.5% chord Max Cl/Cd 72.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe693-il) GOE 693 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 693 airfoil Max thickness 12% at 30% chord Max camber 3.6% at 40% chord Max Cl/Cd 72.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e220-il) E220 (11.48%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E220 low Reynolds number airfoil Max thickness 11.5% at 33.1% chord Max camber 2.2% at 37.7% chord Max Cl/Cd 72.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe490-il) GOE 490 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 490 airfoil Max thickness 8.8% at 19.9% chord Max camber 3.8% at 39.9% chord Max Cl/Cd 72.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe479-il) GOE 479 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 479 airfoil Max thickness 11.6% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 72.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe431-il) GOE 431 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 431 airfoil Max thickness 11.8% at 20% chord Max camber 7.2% at 60% chord Max Cl/Cd 72.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe255-il) GOE 255 (MVA CA.6) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 255 (MVA CA.6) airfoil Max thickness 18.5% at 29.1% chord Max camber 4.8% at 49.1% chord Max Cl/Cd 72.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe142-il) GOE 142 (MVA H.19) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 142 (MVA H.19) airfoil Max thickness 6.2% at 24.9% chord Max camber 3.8% at 34.9% chord Max Cl/Cd 72.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe374-il) GOE 374 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 374 airfoil Max thickness 6.5% at 30% chord Max camber 4.5% at 30% chord Max Cl/Cd 72.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database