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.

(nacam6-il) NACA M6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA M6 airfoil Max thickness 12% at 30% chord Max camber 2.1% at 30% chord Max Cl/Cd 72.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sc1095r8-il) SIKORSKY SC1094R8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky/Velkoff SC1095 R8 rotorcraft airfoil Max thickness 9.3% at 26.5% chord Max camber 2.1% at 20.5% chord Max Cl/Cd 72.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sc1094r8-il) SIKORSKY SC1094 R8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky/Velkoff SC1094 R8 rotorcraft airfoil Max thickness 9.4% at 27.8% chord Max camber 2.1% at 21.7% chord Max Cl/Cd 72.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s819-nr) NREL's S819 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S819 primary 21.0% Dia=10 to 20 m Re=1.0E+6 Clmax(S)=1.20 Clmax(R)=1.16 Restrained max lift coef Max thickness 21.1% at 28.4% chord Max camber 1.3% at 77.3% chord Max Cl/Cd 72.5 at Re# 500,000 Source NWTC National WInd Technology Center
(ag46ct02r-il) AG46ct -02f rot.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG46ct -02f airfoil Max thickness 6.1% at 23.3% chord Max camber 1.6% at 33% chord Max Cl/Cd 72.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(ag46c03-il) AG46c -03f		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG46c -03f airfoil Max thickness 6% at 23.3% chord Max camber 1.9% at 37.3% chord Max Cl/Cd 72.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca63206-il) NACA 63-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-206 airfoil Max thickness 6% at 35% chord Max camber 1.1% at 50% chord Max Cl/Cd 72.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe310-il) GOE 310 (MVA H.42) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 310 (MVA H.42) airfoil Max thickness 8.1% at 29.9% chord Max camber 4.8% at 39.9% chord Max Cl/Cd 72.4 at Re# 500,000 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 72.4 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 72.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database