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.

(pw1211-pw) PW1211		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Peter Wick. Airfoil for plank model gliders Max thickness 7% at 24% chord Max camber 1.7% at 28.2% chord Max Cl/Cd 41.1 at Re# 100,000 Source RC Groups
(s4095-il) S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for micro RC soaring. Used on the E-flite UMX ASK-21 scale RC sailplane. Max thickness 9.7% at 29.1% chord Max camber 1.7% at 33.7% chord Max Cl/Cd 41.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(npl9660-il) NPL 9660 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9660 rotorcraft airfoil Max thickness 11.3% at 34.2% chord Max camber 1% at 19.8% chord Max Cl/Cd 41.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca2421-il) NACA 2421		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2421 airfoil Max thickness 21% at 30% chord Max camber 2% at 40% chord Max Cl/Cd 41.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh110-il) MH 110 10.01%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 110 for stall controlled wind turbines (tip) Max thickness 10% at 23.9% chord Max camber 1% at 15.8% chord Max Cl/Cd 41 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(usa32-il) USA 32 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-32 airfoil Max thickness 14.7% at 19.8% chord Max camber 9.3% at 39.8% chord Max Cl/Cd 41 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe654-il) GOE 654 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 654 airfoil Max thickness 14.5% at 30% chord Max camber 5.2% at 40% chord Max Cl/Cd 41 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ls417-il) NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Whitcomb LS(1)-0417 (GA(W)-1) general aviation airfoil Max thickness 17% at 40% chord Max camber 2.4% at 65% chord Max Cl/Cd 41 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca64206-il) NACA 64-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 41 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh81-il) MH 81 13%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 81 for flying wings (hang glider) Max thickness 12.9% at 25.4% chord Max camber 3.3% at 25.4% chord Max Cl/Cd 41 at Re# 100,000 Source UIUC Airfoil Coordinates Database