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.

(a18sm-il) A18 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Archer A18 F1C free flight airfoil (smoothed) Max thickness 7.3% at 27.1% chord Max camber 3.8% at 49.3% chord Max Cl/Cd 116 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sd7037-il) SD7037-092-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7037 low Reynolds number airfoil Max thickness 9.2% at 26.1% chord Max camber 2.5% at 44.7% chord Max Cl/Cd 116 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe289-il) GOE 289 (MVA 289) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 289 (MVA 289) airfoil Max thickness 16.8% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 115.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe385-il) GOE 385 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 385 airfoil Max thickness 9.9% at 29.9% chord Max camber 4.1% at 29.9% chord Max Cl/Cd 115.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe433-il) GOE 433 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 433 airfoil Max thickness 17.4% at 29.2% chord Max camber 4.8% at 49.2% chord Max Cl/Cd 115.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(usa45-il) USA 45 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-45 airfoil Max thickness 14.5% at 29.8% chord Max camber 4.1% at 29.8% chord Max Cl/Cd 115.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe562-il) GOE 562 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 562 airfoil Max thickness 14.1% at 30% chord Max camber 6.3% at 30% chord Max Cl/Cd 115.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe508-il) GOE 508 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 508 airfoil Max thickness 16.5% at 30% chord Max camber 5.6% at 40% chord Max Cl/Cd 115.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe417-il) GOE 417 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 417 airfoil Max thickness 6% at 20% chord Max camber 6.1% at 40% chord Max Cl/Cd 115.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(be50sm-il) BE50 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Verbitsky BE50 free flight airfoil (original) Max thickness 7.3% at 23.8% chord Max camber 4% at 45.4% chord Max Cl/Cd 115.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database