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.

(sc20403-il) NASA SC(2)-0403 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0403 airfoil (NASA TP-2969) Max thickness 3% at 36% chord Max camber 0.6% at 85% chord Max Cl/Cd 33.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e864-il) EPPLER 864 STRUT AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E864 strut airfoil Max thickness 38.8% at 32.7% chord Max camber 0.1% at 10.8% chord Max Cl/Cd 33.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe561-il) GOE 561 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 561 airfoil Max thickness 25% at 29.8% chord Max camber 10.2% at 29.8% chord Max Cl/Cd 33 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(eiffel10-il) Eiffel 10 (Wright) - 1903 Wright Flyer airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eiffel 10 (Wright) - 1903 Wright Flyer airfoil Max thickness 2.7% at 0% chord Max camber 6.1% at 40% chord Max Cl/Cd 32.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe443-il) GOE 443 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 443 airfoil Max thickness 5% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 32 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe444-il) GOE 444 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 444 airfoil Max thickness 5.6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 31.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(marsden-il) Marsden		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marsden airfoil Max thickness 27.9% at 31.6% chord Max camber 7.7% at 37.6% chord Max Cl/Cd 28.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca16021-il) NACA 16-021		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-021 airfoil Max thickness 21% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 28.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(kenmar-il) KENNEDY AND MARSDEN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Alberta/Kennedy and Marsden high lift airfoil Max thickness 27.9% at 31% chord Max camber 7.7% at 36.9% chord Max Cl/Cd 28.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hs1430-il) HAM-STD HS1-430 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	HS1 family of prop airfoils from US Patent No. 4 Max thickness 30% at 34% chord Max camber 3% at 44% chord Max Cl/Cd 27.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database