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.

(e222-il) E222 (10.17%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E222 low Reynolds number airfoil Max thickness 10.2% at 31.1% chord Max camber 2.1% at 55.3% chord Max Cl/Cd 118.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe281-il) GOE 281 (DAIMLER XII) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 281 (DAIMLER XII) airfoil Max thickness 8% at 30% chord Max camber 4.5% at 40% chord Max Cl/Cd 118.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hobiesm-il) HOBIESMO1.DAT		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hobie Hawk airfoil (Hobie Hawk R/C sailplane) Max thickness 8.6% at 25% chord Max camber 3.8% at 45% chord Max Cl/Cd 118.2 at Re# 1,000,000 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 118.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(be50-il) BE50 (original)		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 25% chord Max camber 4.1% at 45% chord Max Cl/Cd 118.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(n8h12-il) NACA 8-H-12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 8-H-12 rotorcraft airfoil Max thickness 12% at 30% chord Max camber 3.5% at 30% chord Max Cl/Cd 118.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe275-il) GOE 275 (DAIMLER VI) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 275 (DAIMLER VI) airfoil Max thickness 7.7% at 19.9% chord Max camber 4.7% at 29.9% chord Max Cl/Cd 118.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe277-il) GOE 277 (DAIMLER VIII) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 277 (DAIMLER VIII) airfoil Max thickness 8.3% at 29.9% chord Max camber 4.4% at 29.9% chord Max Cl/Cd 118.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe29b-il) GOE 29B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 29B airfoil Max thickness 9.4% at 19.8% chord Max camber 6.5% at 29.8% chord Max Cl/Cd 118.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe574-il) GOE 574 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 574 airfoil Max thickness 10.3% at 30% chord Max camber 4.9% at 40% chord Max Cl/Cd 118.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database