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.

(naca63206-il) NACA 63-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-206 airfoil Max thickness 6% at 35% chord Max camber 1.1% at 50% chord Max Cl/Cd 57 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s102s-il) SOMERS S102 AIRFOIL (SHARP)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dan Somers airfoil for the Toyota general aviation airplane Max thickness 15% at 40% chord Max camber 2.1% at 68.7% chord Max Cl/Cd 57 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e540-il) EPPLER 540 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E540 general aviation airfoil Max thickness 16.9% at 45.5% chord Max camber 1.6% at 35.7% chord Max Cl/Cd 57 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh64-il) MH 64 8.59%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 64 for flying wings Max thickness 8.6% at 26.9% chord Max camber 1.4% at 41.8% chord Max Cl/Cd 57 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ag04-il) AG04		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG04 airfoil Max thickness 6.4% at 22.5% chord Max camber 1.7% at 41.5% chord Max Cl/Cd 57 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(pw75-pw) PW75		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Peter Wick. Modified PW51 with some more reflex Max thickness 8.9% at 27.5% chord Max camber 1.5% at 23.4% chord Max Cl/Cd 57 at Re# 200,000 Source RC Groups
(naca654421-il) NACA 65(4)-421		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(4)-421 airfoil Max thickness 21% at 39.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 57 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e857-il) EPPLER 857 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E857 propeller airfoil Max thickness 20.3% at 31.5% chord Max camber 4.9% at 45.1% chord Max Cl/Cd 56.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e171-il) (Dicke 12.28%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E171 low Reynolds number airfoil Max thickness 12.3% at 32.4% chord Max camber 0% at 0% chord Max Cl/Cd 56.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe744-il) GOE 744 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 744 airfoil Max thickness 14.5% at 20% chord Max camber 7% at 30% chord Max Cl/Cd 56.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database