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.

(usa33-il) USA 33 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-33 airfoil Max thickness 14.2% at 29.9% chord Max camber 4.9% at 29.9% chord Max Cl/Cd 60.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fauvel-il) FAUVEL 14% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Fauvel 14% flying wing airfoil Max thickness 14% at 25.2% chord Max camber 2.5% at 25.2% chord Max Cl/Cd 60.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh62-il) MH 62 9.3%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 62 for flying wings Max thickness 9.3% at 26.9% chord Max camber 1.6% at 36.6% chord Max Cl/Cd 60.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e335-il) EPPLER 335 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E335 flying wing airfoil Max thickness 12.6% at 29% chord Max camber 2.3% at 19.9% chord Max Cl/Cd 60.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe383-il) GOE 383 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 383 airfoil Max thickness 20.2% at 28.7% chord Max camber 5% at 38.7% chord Max Cl/Cd 60.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe421-il) GOE 421 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 421 airfoil Max thickness 19% at 29.3% chord Max camber 8.1% at 49.3% chord Max Cl/Cd 60.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ag19-il) AG19		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG19 airfoil Max thickness 5.4% at 20.6% chord Max camber 2.2% at 44.2% chord Max Cl/Cd 60.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(marske1-il) MARSKE XM-1D AIRFOIL (F14-3.0)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marske XM-1D airfoil (F14-3.0) Max thickness 14% at 25.1% chord Max camber 3% at 25.1% chord Max Cl/Cd 60.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca24112-jf) NACA 24112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 24112 5 digit reflex airfoil Max thickness 12% at 29.4% chord Max camber 1.7% at 20.6% chord Max Cl/Cd 60.4 at Re# 200,000 Source Javafoil generated
(ag17-il) AG17		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG17 airfoil Max thickness 6.5% at 22.1% chord Max camber 2% at 45.5% chord Max Cl/Cd 60.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database