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.

(fx62k131-il) WORTMANN FX 62-K-131 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 62-K-131/17 airfoil Max thickness 13.1% at 40.2% chord Max camber 3.9% at 53.3% chord Max Cl/Cd 30.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(avistar-il) AVISTAR		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hobbico R/C Avistar trainer airfoil Max thickness 14.5% at 34.2% chord Max camber 2.3% at 37.9% chord Max Cl/Cd 30.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe598-il) GOE 598 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 598 airfoil Max thickness 6.5% at 39.8% chord Max camber 1% at 49.8% chord Max Cl/Cd 30.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(nacam6-il) NACA M6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA M6 airfoil Max thickness 12% at 30% chord Max camber 2.1% at 30% chord Max Cl/Cd 30.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq3015-il) HQ 3.0/15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/15 R/C sailplane airfoil Max thickness 15% at 35% chord Max camber 3% at 50% chord Max Cl/Cd 30.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(goe615-il) GOE 615 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 615 airfoil Max thickness 13.7% at 29.7% chord Max camber 5.6% at 39.7% chord Max Cl/Cd 30.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e559-il) EPPLER 559 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E559 general aviation airfoil Max thickness 16% at 27.2% chord Max camber 4.3% at 50.2% chord Max Cl/Cd 30.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fg4-il) Fage & Collins 4		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Fage & Collins 4 airfoil Max thickness 12.7% at 30% chord Max camber 4.7% at 30% chord Max Cl/Cd 30.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(c5c-il) LOCKHEED C-5A BL576 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.1% at 40% chord Max camber 1.4% at 65% chord Max Cl/Cd 30.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(vr11x-il) BOEING-VERTOL VR-11X AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol/NASA/Dadone VR-11X transonic rotorcraft airfoil Max thickness 11% at 40% chord Max camber 2.4% at 25% chord Max Cl/Cd 30.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database