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.

(mh38-il) MH 38 9.68%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 38 for Endurance Model Max thickness 9.7% at 31.6% chord Max camber 3.9% at 45.3% chord Max Cl/Cd 149.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(r1046-il) RONCZ 1046 VOYAGER CANARD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1046 Voyager canard airfoil Max thickness 18.1% at 38% chord Max camber 6.7% at 42% chord Max Cl/Cd 149.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(la5055-il) LIEBECK LA5055 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Liebeck high lift airfoil Max thickness 15.9% at 35% chord Max camber 5.9% at 40% chord Max Cl/Cd 149.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(lnv109a-il) LNV109A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Douglas/Liebeck LNV109A high lift airfoil Max thickness 13% at 23.5% chord Max camber 6% at 31.5% chord Max Cl/Cd 149.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s802-nr) NREL's S802 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S802 tip Not recommended Max thickness 11.5% at 37.9% chord Max camber 3.8% at 47.3% chord Max Cl/Cd 149.5 at Re# 1,000,000 Source NWTC National WInd Technology Center

(ah80140-il) AH 80-140		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 80-140 airfoil Max thickness 14% at 30.9% chord Max camber 4.4% at 33.9% chord Max Cl/Cd 149.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx77w121-il) FX 77-W-121		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 77-W-121 airfoil for use on wind turbines (W) Max thickness 12.1% at 30.9% chord Max camber 4.6% at 30.9% chord Max Cl/Cd 149.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(drgnfly-il) DRAGONFLY CANARD		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dragonfly Canard airfoil Max thickness 19.3% at 37.6% chord Max camber 6.6% at 40.9% chord Max Cl/Cd 149.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(r1046-il) RONCZ 1046 VOYAGER CANARD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1046 Voyager canard airfoil Max thickness 18.1% at 38% chord Max camber 6.7% at 42% chord Max Cl/Cd 148.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx66s161-il) FX 66-S-161 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-S-161 airfoil Max thickness 16.1% at 33.9% chord Max camber 3.9% at 43.5% chord Max Cl/Cd 148.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database