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.

(coanda1-il) Coanda 1		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Coanda 1 airfoil Max thickness 5.7% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 63.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(supermarine371ii-il) Supermarine 371-II (tip)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Supermarine 371-II tip airfoil Max thickness 8.4% at 50% chord Max camber 0.9% at 45% chord Max Cl/Cd 63.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(p51dtip-il) P-51D TIP (BL215) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	P-51D tip (BL215) airfoil Max thickness 11.4% at 46.3% chord Max camber 1.3% at 46.3% chord Max Cl/Cd 63.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca0012h-sa) NACA0012H for VAWT from Sandia report SAND80-2114		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Modified Naca 0012 airfoil for Sandia VAWT tests Max thickness 12.2% at 22.5% chord Max camber 0% at 0% chord Max Cl/Cd 63.7 at Re# 500,000 Source Sandia National Laboratories
(sc20710-il) NASA SC(2)-0710 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0710 airfoil (NASA TP-2969) Max thickness 10% at 37% chord Max camber 2.1% at 81% chord Max Cl/Cd 63.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(sc20612-il) NASA SC(2)-0612 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0612 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 1.9% at 81% chord Max Cl/Cd 63.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca1410-il) NACA 1410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 1410 airfoil Max thickness 10% at 29.9% chord Max camber 1% at 50% chord Max Cl/Cd 63.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe522-il) GOE 522 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 522 airfoil Max thickness 21.8% at 28.6% chord Max camber 5.2% at 48.7% chord Max Cl/Cd 63.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(k1-il) NYU/GRUMMAN K-1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NYU/Grumman K-1 transonic airfoil (GAC .75-.63-11.6) Max thickness 11.6% at 33% chord Max camber 1.9% at 75% chord Max Cl/Cd 63.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n64110-il) NACA 64-110 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-110 airfoil Max thickness 10% at 40% chord Max camber 0.6% at 50% chord Max Cl/Cd 63.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database