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.

(sc20402-il) NASA SC(2)-0402 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0402 airfoil (NASA TP-2969) Max thickness 2% at 34% chord Max camber 0.5% at 83% chord Max Cl/Cd 14.2 at Re# 50,000 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 14.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n5h15-il) NACA 5-H-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 5-H-15 rotorcraft airfoil Max thickness 15.4% at 40% chord Max camber 2.9% at 30% chord Max Cl/Cd 14.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx05188-il) WORTMANN FX 05-188 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 05-188 airfoil Max thickness 18.8% at 37.1% chord Max camber 2.6% at 50% chord Max Cl/Cd 14.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e1098-il) EPPLER 1098 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1098 general aviation airfoil Max thickness 18.9% at 36.6% chord Max camber 3.7% at 54.5% chord Max Cl/Cd 14.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(usa31-il) USA 31 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-31 airfoil Max thickness 14.8% at 19.7% chord Max camber 9.3% at 39.7% chord Max Cl/Cd 14.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx76mp140-il) FX 76-MP-140		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 76-MP-140 airfoil Max thickness 14.1% at 33.9% chord Max camber 7.1% at 46.7% chord Max Cl/Cd 14.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe741-il) GOE 741 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 741 airfoil Max thickness 15.3% at 30% chord Max camber 4.8% at 30% chord Max Cl/Cd 14.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(m26-il) NACA M26 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-26 airfoil Max thickness 8.3% at 40% chord Max camber 8.3% at 30% chord Max Cl/Cd 14 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe530-il) GOE 530 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 530 airfoil Max thickness 12.9% at 29.8% chord Max camber 5.1% at 29.8% chord Max Cl/Cd 14 at Re# 50,000 Source UIUC Airfoil Coordinates Database