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.

(fx73cl1152-il) FX 73-CL1-152		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 73-CL1-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 6.1% at 33.9% chord Max Cl/Cd 42.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh106-il) MH 106 13.07%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 106 for stall controlled wind turbines Max thickness 13.1% at 27.4% chord Max camber 0.9% at 27.4% chord Max Cl/Cd 42.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e340-il) EPPLER 340 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E340 flying wing airfoil Max thickness 13.7% at 28.8% chord Max camber 2.6% at 19.7% chord Max Cl/Cd 42.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(npl9615-il) NPL 9615 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9615 rotorcraft airfoil Max thickness 11.3% at 34.2% chord Max camber 1% at 19.8% chord Max Cl/Cd 42.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh82-il) MH 82 13.31%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 82 for flying wings (hang glider) Max thickness 13.3% at 24.6% chord Max camber 3.9% at 24.6% chord Max Cl/Cd 42.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(c141a-il) LOCKHEED C-141 BL0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 13% at 40.2% chord Max camber 1.1% at 64.5% chord Max Cl/Cd 42 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe766-il) GOE 766 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 766 airfoil Max thickness 12% at 25% chord Max camber 1.5% at 20% chord Max Cl/Cd 42 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e904-il) EPPLER 904 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E904 hydrofoil Max thickness 9% at 44.9% chord Max camber 1.3% at 50.4% chord Max Cl/Cd 41.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e587-il) EPPLER 587 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E587 sailplane airfoil Max thickness 16.6% at 41.1% chord Max camber 4.2% at 51.2% chord Max Cl/Cd 41.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e1212-il) EPPLER E1212 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1212 general aviation airfoil Max thickness 17.7% at 23.4% chord Max camber 3.2% at 36.4% chord Max Cl/Cd 41.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database