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.

(raf27-il) RAF 27 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-27 airfoil Max thickness 9.8% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 56.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(m3-il) NACA M3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-3 airfoil Max thickness 11.9% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 56.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(nacam3-il) NACA M3		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA M3 airfoil Max thickness 11.9% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 56.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca65206-il) NACA 65-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 56.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sc20412-il) NASA SC(2)-0412 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0412 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 1.3% at 83% chord Max Cl/Cd 56.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(bqm34-il) RYAN BQM-34 FIREBEE WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Ryan BQM-34 Firebee wing airfoil (NACA 63-014A W/NACA 0014 nose and thinned to .09899 to account for sweep) Max thickness 9.9% at 32.5% chord Max camber 0% at 0% chord Max Cl/Cd 56.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe775-il) GOE 775 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 775 airfoil Max thickness 21% at 30% chord Max camber 0% at 1.3% chord Max Cl/Cd 56.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sc20010-il) NASA SC(2)-0010 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0010 airfoil (NASA TP-2969) Max thickness 10% at 37% chord Max camber 0% at 0% chord Max Cl/Cd 56.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(chen-il) CHEN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Illinois at Urbana-Champaign / Chen high lift airfoil Max thickness 12.5% at 27.7% chord Max camber 7.8% at 25.4% chord Max Cl/Cd 56.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n64012-il) NASA/LANGLEY 64-012 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-012 airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 56.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database