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.

(n2415-il) NACA 2415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2415 airfoil Max thickness 15% at 29.5% chord Max camber 2% at 39.6% chord Max Cl/Cd 47.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca2415-il) NACA 2415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2415 airfoil Max thickness 15% at 30% chord Max camber 2% at 40% chord Max Cl/Cd 47.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(eiffel430-il) Eiffel 430 (Lachassgne)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eiffel 430 (Lachassgne) airfoil Max thickness 9.7% at 15% chord Max camber 4.5% at 40% chord Max Cl/Cd 47.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe285-il) GOE 285 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 285 airfoil Max thickness 11.7% at 30% chord Max camber 3.7% at 30% chord Max Cl/Cd 47.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(c141d-il) LOCKHEED C-141 BL610.61 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 10.8% at 40.2% chord Max camber 1.5% at 50% chord Max Cl/Cd 47.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(e668-il) EPPLER 668 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E668 sailplane airfoil Max thickness 13.9% at 37.3% chord Max camber 4% at 47.8% chord Max Cl/Cd 47.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(stcyr234-il) St. CYR 234 (Bartel 17-IC)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	St. CYR 234 (Bartel 17-IC) airfoil Max thickness 16% at 20% chord Max camber 5.1% at 50% chord Max Cl/Cd 47.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(raf15-il) RAF 15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-15 airfoil Max thickness 6.5% at 15% chord Max camber 2.6% at 30% chord Max Cl/Cd 47.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh61-il) MH 61 10.26%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 61 for flying wings Max thickness 10.2% at 27.6% chord Max camber 1.4% at 37.3% chord Max Cl/Cd 47.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e332-il) EPPLER 332 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E332 flying wing airfoil Max thickness 11.5% at 32.3% chord Max camber 3.1% at 22.6% chord Max Cl/Cd 47.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database