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.

(e850-il) EPPLER E850 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E850 propeller airfoil Max thickness 8% at 36.6% chord Max camber 1.8% at 71% chord Max Cl/Cd 97.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe393-il) GOE 393 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 393 airfoil Max thickness 6.1% at 19.9% chord Max camber 4.2% at 29.9% chord Max Cl/Cd 97.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s1223-il) S1223		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1223 high lift low Reynolds number airfoil Max thickness 12.1% at 19.8% chord Max camber 8.1% at 49% chord Max Cl/Cd 97.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe385-il) GOE 385 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 385 airfoil Max thickness 9.9% at 29.9% chord Max camber 4.1% at 29.9% chord Max Cl/Cd 97.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e338-il) EPPLER 338 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E338 flying wing airfoil Max thickness 13.3% at 31.1% chord Max camber 3.7% at 26.2% chord Max Cl/Cd 97.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe682-il) GOE 682 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 682 airfoil Max thickness 10.7% at 30% chord Max camber 4.3% at 40% chord Max Cl/Cd 97.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s825-nr) NREL's S825 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S825 primary 17.0% Dia=20 to 40 m Re=2.0E+6 Clmax(S)=1.44 Clmax(R)=1.37 High max lift coef Max thickness 17.1% at 29.9% chord Max camber 3.9% at 65.3% chord Max Cl/Cd 97.4 at Re# 500,000 Source NWTC National WInd Technology Center
(ste87391-il) EPPLER STE 87(-3)-914 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler STE 87(-3)-914 airfoil Max thickness 14.6% at 34.1% chord Max camber 4.2% at 58.3% chord Max Cl/Cd 97.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe422-il) GOE 422 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 422 airfoil Max thickness 17.1% at 29.5% chord Max camber 6.5% at 39.5% chord Max Cl/Cd 97.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe79-il) GOE 79 (PFALZ 11) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 79 (Pfalz 11) airfoil Max thickness 6.2% at 14.9% chord Max camber 6% at 29.9% chord Max Cl/Cd 97.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database