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.

(goe676-il) GOE 676 (= M 12) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 676 (= M 12) airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord Max Cl/Cd 48.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx60160-il) FX 60-160 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-160 airfoil Max thickness 15.6% at 40% chord Max camber 3.1% at 60% chord Max Cl/Cd 48.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s8064-il) S8064		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for Q-500 (Q500) pylon racing (12.33%). Used on the Great Planes Viper 500 ARF. Max thickness 12.3% at 37.8% chord Max camber 1.1% at 56.2% chord Max Cl/Cd 48.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe617-il) GOE 617 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 617 airfoil Max thickness 13.9% at 30% chord Max camber 2.2% at 30% chord Max Cl/Cd 48.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s2055-il) S2055		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2055 low Reynolds number airfoil Max thickness 8% at 34.8% chord Max camber 1.4% at 44.6% chord Max Cl/Cd 48.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(m12-il) NACA M12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-12 airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord Max Cl/Cd 48.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s2050-il) S2050 8.93%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2050 low Reynolds number airfoil Max thickness 8.9% at 29.8% chord Max camber 1.1% at 69.5% chord Max Cl/Cd 48.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(b737d-il) BOEING 737 OUTBOARD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company model 737 airfoils Max thickness 10.8% at 40% chord Max camber 1.6% at 20% chord Max Cl/Cd 48.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fg3-il) Fage & Collins 3		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Fage & Collins 3 airfoil Max thickness 10.1% at 30% chord Max camber 4.3% at 30% chord Max Cl/Cd 48.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rg149-il) RG 14 9% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 14 (9%) airfoil Max thickness 9% at 31% chord Max camber 1.6% at 36% chord Max Cl/Cd 48.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database