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.

(uag8814320-il) UAG 88-143/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	UAG 88-143/20 airfoil Max thickness 14.3% at 43.5% chord Max camber 6.2% at 46.7% chord Max Cl/Cd 15.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca66-018-il) NACA 66-018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66-018 airfoil Max thickness 18% at 45% chord Max camber 0% at 0% chord Max Cl/Cd 15.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe190-il) GOE 190 (MVA MK.18) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 190 (MVA MK.18) airfoil Max thickness 12.7% at 19.7% chord Max camber 5.9% at 49.7% chord Max Cl/Cd 15.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca653618-il) NACA 65(3)-618		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(3)-618 airfoil Max thickness 18% at 39.8% chord Max camber 3.3% at 50% chord Max Cl/Cd 15.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca4421-il) NACA 4421		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4421 airfoil Max thickness 21% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 15.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(mh84-il) MH 84 13.69%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 84 for flying wings (hang glider) Max thickness 13.7% at 21.5% chord Max camber 4.1% at 36.6% chord Max Cl/Cd 15.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe255-il) GOE 255 (MVA CA.6) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 255 (MVA CA.6) airfoil Max thickness 18.5% at 29.1% chord Max camber 4.8% at 49.1% chord Max Cl/Cd 15.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe404-il) GOE 404 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 404 airfoil Max thickness 13.2% at 29.6% chord Max camber 5% at 29.6% chord Max Cl/Cd 15.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ua79sf18-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Alberta/Marsden UA 79-SF-187 FLAPPED sailplane airfoil Max thickness 18.8% at 42.8% chord Max camber 3.7% at 63.4% chord Max Cl/Cd 15.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx61184-il) FX 61-184 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 61-184 airfoil Max thickness 18.4% at 37.1% chord Max camber 3.1% at 62.9% chord Max Cl/Cd 15.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database