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.

(mh93-il) MH 93 15.98%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 93 parafoil Max thickness 16% at 27.6% chord Max camber 1.4% at 15.2% chord Max Cl/Cd 24.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe593-il) GOE 593 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 593 airfoil Max thickness 11.9% at 30% chord Max camber 4.1% at 40% chord Max Cl/Cd 24.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx84w127-il) FX 84-W-127		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 84-W-127 airfoil for use on wind turbines (W) Max thickness 12.8% at 33.9% chord Max camber 3.7% at 40.2% chord Max Cl/Cd 24.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n64212mb-il) NACA 64(1)-212 MOD B		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA-NASA/AMES/Hicks 63(1)-212 MOD B airfoil Max thickness 12% at 34.9% chord Max camber 1.5% at 9.9% chord Max Cl/Cd 24.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ls417mod-il) NASA/LANGLEY LS(1)-0417MOD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0417MOD general aviation airfoil Max thickness 17% at 30.2% chord Max camber 2.3% at 20.2% chord Max Cl/Cd 24.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(vr9-il) BOEING-VERTOL VR-9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-9 rotorcraft airfoil Max thickness 6.1% at 35% chord Max camber 0.3% at 35% chord Max Cl/Cd 24.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e343-il) EPPLER 343 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E343 flying wing airfoil Max thickness 14.5% at 30.9% chord Max camber 4% at 26% chord Max Cl/Cd 24.3 at Re# 50,000 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 24.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rhodesg32-il) Rhode St. Genese 32		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rhode St. Genese 32 airfoil Max thickness 11.9% at 30% chord Max camber 3.9% at 40% chord Max Cl/Cd 24.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe118-il) GOE 118 (MVA MK.7) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 118 (MVA MK.7) airfoil Max thickness 8.6% at 29.9% chord Max camber 5.7% at 39.9% chord Max Cl/Cd 24.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database