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.

(la203a-il) DOUGLAS LA203A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Douglas/Liebeck LA203A high lift airfoil Max thickness 15.7% at 34.3% chord Max camber 5.5% at 46% chord Max Cl/Cd 46.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe289-il) GOE 289 (MVA 289) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 289 (MVA 289) airfoil Max thickness 16.8% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 46.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca633618-il) NACA 63(3)-618		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(3)-618 airfoil Max thickness 18% at 34.7% chord Max camber 3.3% at 50% chord Max Cl/Cd 46.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx63143-il) FX 63-143 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-143 airfoil Max thickness 14.3% at 33.9% chord Max camber 3.1% at 30.9% chord Max Cl/Cd 46.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe416a-il) GOE 416A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 416A airfoil Max thickness 11.7% at 29.5% chord Max camber 1.3% at 59.6% chord Max Cl/Cd 46.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(rg1410-il) RG 14 10% 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 (10%) airfoil Max thickness 10% at 31% chord Max camber 1.6% at 36% chord Max Cl/Cd 46.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe14-il) GOE 14 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 14 airfoil Max thickness 9.9% at 29.8% chord Max camber 6.9% at 29.8% chord Max Cl/Cd 46.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(c5e-il) LOCKHEED C-5A BL1256 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 10.8% at 40% chord Max camber 1.4% at 30% chord Max Cl/Cd 46.4 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 46.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ms313-il) NASA/LANGLEY MS(1)-0313 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley MS(1)-0313 general aviation airfoil (buggy Max thickness 13.1% at 37.5% chord Max camber 1.8% at 67.5% chord Max Cl/Cd 46.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database