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.

(fxs21158-il) FX S 02/1-158 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX S 02/1-158 airfoil Max thickness 15.8% at 30.9% chord Max camber 3.5% at 37.1% chord Max Cl/Cd 37.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(lwk79100-il) LWK 79-100		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LWK 79-100 symmetrical airfoil Max thickness 10% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 37.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca747a415-il) NACA 747A415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 747A415 airfoil Max thickness 15% at 40.2% chord Max camber 3% at 35% chord Max Cl/Cd 37.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca24112-jf) NACA 24112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 24112 5 digit reflex airfoil Max thickness 12% at 29.4% chord Max camber 1.7% at 20.6% chord Max Cl/Cd 37.3 at Re# 100,000 Source Javafoil generated
(fx60177-il) FX 60-177 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-177 airfoil Max thickness 17.7% at 37.1% chord Max camber 2.7% at 77.8% chord Max Cl/Cd 37.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(n0009sm-il) NACA-0009 9.0% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0009 airfoil (smoothed) Max thickness 9% at 30.9% chord Max camber 0% at 0% chord Max Cl/Cd 37.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe459-il) GOE 459 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 459 airfoil Max thickness 12.7% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 37.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx76mp140-il) FX 76-MP-140		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 76-MP-140 airfoil Max thickness 14.1% at 33.9% chord Max camber 7.1% at 46.7% chord Max Cl/Cd 37.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s1012-il) S1012		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1012 HPV airfoil Max thickness 12% at 37.3% chord Max camber 0% at 0% chord Max Cl/Cd 37.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(joukowsk-il) 12% JOUKOWSKI AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	12% Joukowski airfoil Max thickness 11.8% at 25% chord Max camber 0% at 9.5% chord Max Cl/Cd 37.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database