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.

(falcon-il) Falcon		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Falcon airfoil used on the Carl Goldberg Falcon 56 Mk II R/C powerplane Max thickness 13.7% at 30.6% chord Max camber 1.6% at 20.5% chord Max Cl/Cd 78.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n5h20-il) NACA 5-H-20 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 5-H-20 rotorcraft airfoil Max thickness 19.9% at 40% chord Max camber 4.5% at 40% chord Max Cl/Cd 78.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hq108-il) HQ 1.0/8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.0/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 1% at 50% chord Max Cl/Cd 78.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(glennmartin2-il) Glenn Martin 2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Glenn Martin 2 airfoil Max thickness 13.5% at 20% chord Max camber 6.1% at 30% chord Max Cl/Cd 78.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca654221-il) NACA 65(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(4)-221 airfoil Max thickness 21% at 39.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 78.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(e542-il) EPPLER 542 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E542 general aviation airfoil Max thickness 16.9% at 41.3% chord Max camber 1.9% at 31.5% chord Max Cl/Cd 78.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(mh42-il) MH 42 8.94%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 42 low Reynolds number airfoil Max thickness 8.9% at 31.3% chord Max camber 1.8% at 36.3% chord Max Cl/Cd 78.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(supermarine371i-il) Supermarine 371-I (root)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Supermarine 371-I root airfoil Max thickness 13% at 40% chord Max camber 0.9% at 50% chord Max Cl/Cd 78.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sd7003-il) SD7003-085-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7003 low Reynolds number airfoil Max thickness 8.5% at 24.4% chord Max camber 1.2% at 38.3% chord Max Cl/Cd 78.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe704-il) GOE 704 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 704 airfoil Max thickness 12.9% at 29.9% chord Max camber 2.1% at 39.9% chord Max Cl/Cd 78.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database