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.

(lds2-il) LDS-2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LDS-2 airfoil Max thickness 12% at 34.9% chord Max camber 2.2% at 45% chord Max Cl/Cd 77.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ls413mod-il) NASA/LANGLEY LS(1)-0413MOD 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)-0413MOD general aviation airfoil Max thickness 13% at 35% chord Max camber 2.2% at 40% chord Max Cl/Cd 77.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe564-il) GOE 564 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 564 airfoil Max thickness 8.2% at 30% chord Max camber 2.7% at 40% chord Max Cl/Cd 77.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(cap21c-il) CAP 21 (TraCFoil)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CAP 21 (TraCFoil) airfoil Max thickness 15.6% at 15.7% chord Max camber 0.6% at 23.9% chord Max Cl/Cd 77.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe572-il) GOE 572 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 572 airfoil Max thickness 18.6% at 29.9% chord Max camber 8.3% at 29.9% chord Max Cl/Cd 77.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(mh60-il) MH 60 10.08%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 60 for flying wings Max thickness 10.1% at 26.9% chord Max camber 1.7% at 36.6% chord Max Cl/Cd 77.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(marske2-il) MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYBRID)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marske Pioneer IA airfoil (NACA 23112/43012A hybrid) Max thickness 12.1% at 25% chord Max camber 2.7% at 15% chord Max Cl/Cd 77.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ah94w301-il) AH 94-W-301		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 94-W-301 airfoil for use on wind turbines (W) Max thickness 30.1% at 30.9% chord Max camber 1.3% at 80.4% chord Max Cl/Cd 77.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s823-nr) NREL's S823 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S823 root 21.0% Dia=2 to 10 m Re=4.0E+5 Clmax(S)=1.20 Clmax(R)=1.16 Restrained max lift coef Max thickness 21.2% at 24.3% chord Max camber 2.4% at 70.5% chord Max Cl/Cd 77.5 at Re# 500,000 Source NWTC National WInd Technology Center
(s835-nr) NREL's S835 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S835 root 21.0% Dia=1 to 3 m Re=2.5E+5 Clmax(S)=1.20 Clmax(R)=1.03 High max lift coef Max thickness 21% at 30.5% chord Max camber 2.4% at 78% chord Max Cl/Cd 77.4 at Re# 500,000 Source NWTC National WInd Technology Center