Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(fx66182-il) FX 66-182 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-182 airfoil Max thickness 18.2% at 33.9% chord Max camber 3.8% at 37.1% chord Max Cl/Cd 128.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe437-il) GOE 437 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 437 airfoil Max thickness 7.1% at 30% chord Max camber 4.8% at 40% chord Max Cl/Cd 128.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s4022-il) S4022		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4022 low Reynolds number airfoil Max thickness 11.3% at 34.1% chord Max camber 4.3% at 57.8% chord Max Cl/Cd 128.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe330-il) GOE 330 (PFALZ 59) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 330 (Pfalz 59) airfoil Max thickness 10.2% at 29.9% chord Max camber 5.8% at 39.9% chord Max Cl/Cd 128.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s804-nr) NREL's S804 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S804 root Not recommended Max thickness 17.9% at 26.7% chord Max camber 4.2% at 39.6% chord Max Cl/Cd 128 at Re# 1,000,000 Source NWTC National WInd Technology Center

(goe269-il) GOE 269 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 269 airfoil Max thickness 6.6% at 29.9% chord Max camber 5% at 39.9% chord Max Cl/Cd 127.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e554-il) EPPLER 554 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E554 general aviation airfoil Max thickness 18.2% at 31.8% chord Max camber 2.7% at 56.6% chord Max Cl/Cd 127.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e603-il) EPPLER 603 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E603 general purpose airfoil Max thickness 19% at 40% chord Max camber 3.6% at 35.6% chord Max Cl/Cd 127.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe480-il) GOE 480 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 480 airfoil Max thickness 11.8% at 30% chord Max camber 5.5% at 40% chord Max Cl/Cd 127.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe362-il) GOE 362 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 362 airfoil Max thickness 6.6% at 20% chord Max camber 5.3% at 40% chord Max Cl/Cd 127.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database