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.

(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 16.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx66s161-il) FX 66-S-161 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-S-161 airfoil Max thickness 16.1% at 33.9% chord Max camber 3.9% at 43.5% chord Max Cl/Cd 16.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx057816-il) WORTMANN FX 057-816		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 057-816 airfoil Max thickness 16.2% at 37.1% chord Max camber 5.1% at 37.1% chord Max Cl/Cd 16.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca654421a05-il) NACA 65(4)-421 a=0.5		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(4)-421 a=0.5 airfoil Max thickness 21% at 39.9% chord Max camber 3% at 45% chord Max Cl/Cd 16.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(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 16.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(la2573a-il) LA2573A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Liebeck LA2573A airfoil Max thickness 13.7% at 28.8% chord Max camber 3.2% at 26.1% chord Max Cl/Cd 15.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(la5055-il) LIEBECK LA5055 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Liebeck high lift airfoil Max thickness 15.9% at 35% chord Max camber 5.9% at 40% chord Max Cl/Cd 15.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe777-il) GOE 777 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 777 airfoil Max thickness 22% at 30% chord Max camber 5.9% at 30% chord Max Cl/Cd 15.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n66021-il) NACA 66-021 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(4)-021 airfoil Max thickness 21% at 45% chord Max camber 0% at 0% chord Max Cl/Cd 15.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(th25816-il) TH 25816 HALE AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Naval Air Development Center/Doug Hall high altitude Max thickness 25.7% at 48.3% chord Max camber 4% at 52.9% chord Max Cl/Cd 15.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database