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.

(fx68h120-il) FX 68-H-120		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 68-H-120 airfoil Max thickness 11.8% at 25% chord Max camber 2.3% at 33.9% chord Max Cl/Cd 54.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s815-nr) NREL's S815 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S815 root 26.0% Dia=20 to 30 m Re=1.2E+6 Clmax(S)=1.46 Clmax(R)=1.40 High max lift coef Max thickness 26.2% at 25.7% chord Max camber 2.9% at 77.9% chord Max Cl/Cd 54.4 at Re# 200,000 Source NWTC National WInd Technology Center
(e361-il) EPPLER 361 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E361 rotorcraft airfoil Max thickness 12.1% at 37.1% chord Max camber 1.7% at 27.4% chord Max Cl/Cd 54.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca641112-il) NACA 64(1)-112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-112 airfoil Max thickness 12% at 40% chord Max camber 0.6% at 50% chord Max Cl/Cd 54.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(vr14-il) BOEING-VERTOL VR-14 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol/Dadone VR-14 rotorcraft airfoil Max thickness 8% at 35% chord Max camber 1.7% at 20% chord Max Cl/Cd 54.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(ncambre-il) ONERA NACA CAMBRE AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale NACA-CAMBRE rotorcraft airfoil Max thickness 11.5% at 31.2% chord Max camber 1.4% at 15.9% chord Max Cl/Cd 54.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(npl9627-il) NPL 9627 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9627 rotorcraft airfoil Max thickness 12.2% at 31% chord Max camber 0.9% at 40.4% chord Max Cl/Cd 54.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx68h120-il) FX 68-H-120		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 68-H-120 airfoil Max thickness 11.8% at 25% chord Max camber 2.3% at 33.9% chord Max Cl/Cd 54.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(stf86361-il) EPPLER STF 863-615 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler STF 863-615 airfoil Max thickness 14.7% at 44.7% chord Max camber 4.2% at 72.3% chord Max Cl/Cd 54.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe679-il) GOE 679 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 679 airfoil Max thickness 18.3% at 29.1% chord Max camber 4.5% at 39.1% chord Max Cl/Cd 54.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database