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 21.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s831-nr) NREL's S831 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S831 tip 18.0% Dia=40 to 50 m Re=3.5E+6 Clmax(S)=1.50 Clmax(R)=1.48 High max lift coef Max thickness 18% at 44.2% chord Max camber 5% at 53.1% chord Max Cl/Cd 21.8 at Re# 100,000 Source NWTC National WInd Technology Center
(marske1-il) MARSKE XM-1D AIRFOIL (F14-3.0)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marske XM-1D airfoil (F14-3.0) Max thickness 14% at 25.1% chord Max camber 3% at 25.1% chord Max Cl/Cd 21.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca16006-il) NACA 16-006		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-006 airfoil Max thickness 6% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 21.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(r1082-il) RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1082 Voyager root outer aft wing airfoil Max thickness 18% at 40% chord Max camber 3.4% at 40% chord Max Cl/Cd 21.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(e858-il) EPPLER 858 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E858 propeller airfoil Max thickness 22.7% at 26.6% chord Max camber 4.7% at 44.3% chord Max Cl/Cd 21.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(nlr7301-il) NLR-7301 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NLR NLR-7301 transonic airfoil Max thickness 16.5% at 35% chord Max camber 1.7% at 75% chord Max Cl/Cd 21.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx69pr281-il) FX 69-PR-281		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 69-PR-281 airfoil Max thickness 28.1% at 22.2% chord Max camber 5.6% at 50% chord Max Cl/Cd 21.5 at Re# 100,000 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 21.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca654221-il) NACA 65(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(4)-221 airfoil Max thickness 21% at 39.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 21.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database