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.

(s4061-il) S4061-096-84		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4061 low Reynolds number airfoil Max thickness 9.6% at 30.9% chord Max camber 3.3% at 44.7% chord Max Cl/Cd 59.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe430-il) GOE 430 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 430 airfoil Max thickness 13.4% at 29.5% chord Max camber 4.8% at 49.6% chord Max Cl/Cd 59.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(usa98-il) USA 98 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-98 airfoil Max thickness 14.3% at 30% chord Max camber 6.4% at 50% chord Max Cl/Cd 59.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e853-il) EPPLER E853 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E853 propeller airfoil Max thickness 11.6% at 37.1% chord Max camber 3.1% at 56.1% chord Max Cl/Cd 59.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe226-il) GOE 226 (MVA H.36) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 226 (MVA H.36) airfoil Max thickness 13.9% at 19.7% chord Max camber 8.1% at 49.7% chord Max Cl/Cd 59.7 at Re# 100,000 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 59.7 at Re# 100,000 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 59.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s7075-il) S7075 (9%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S7075 low Reynolds number airfoil Max thickness 9% at 29% chord Max camber 2.8% at 46.8% chord Max Cl/Cd 59.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe310-il) GOE 310 (MVA H.42) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 310 (MVA H.42) airfoil Max thickness 8.1% at 29.9% chord Max camber 4.8% at 39.9% chord Max Cl/Cd 59.6 at Re# 100,000 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 59.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database