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.

(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 41.5 at Re# 200,000 Source Sandia National Laboratories
(fx79l100-il) FX 79-L-100		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 79-L-100 symmetrical airfoil Max thickness 10.1% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 41.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca663218-il) NACA 66(3)-218		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(3)-218 airfoil Max thickness 18% at 45% chord Max camber 1.1% at 50% chord Max Cl/Cd 41.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(rae102-il) RAE 102 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 102 airfoil Max thickness 10% at 36% chord Max camber 0% at 0% chord Max Cl/Cd 41.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(lwk80120k25-il) LWK 80-120/K25		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LWK 80-120/K25 symmetrical airfoil Max thickness 12.1% at 40.2% chord Max camber 0% at 0% chord Max Cl/Cd 41.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(e472-il) EPPLER 472 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E472 aerobatic aircraft airfoil Max thickness 12.1% at 17.5% chord Max camber 0% at 0% chord Max Cl/Cd 41.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hq010-il) HQ 0/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 0/10 R/C sailplane airfoil Max thickness 10% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 41.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca23024-il) NACA 23024		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23024 airfoil Max thickness 24% at 30.3% chord Max camber 2.9% at 1.3% chord Max Cl/Cd 41.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sc20410-il) NASA SC(2)-0410 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0410 airfoil (NASA TP-2969) Max thickness 10% at 38% chord Max camber 1.1% at 85% chord Max Cl/Cd 41.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(rcsc2-il) NASA/LANGLEY RC-SC2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-SC2 rotorcraft airfoil Max thickness 10% at 40% chord Max camber 0.5% at 62.5% chord Max Cl/Cd 41.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database