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.

(naca2424-il) NACA 2424		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2424 airfoil Max thickness 24% at 29.7% chord Max camber 2% at 40% chord Max Cl/Cd 40.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx711530-il) FX 71-L-150/30 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 71-L-150/30 airfoil Max thickness 15% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 40.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx71l150-il) FX 71-L-150/30 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 71-L-150/30 airfoil Max thickness 15% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 40.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sc20402-il) NASA SC(2)-0402 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0402 airfoil (NASA TP-2969) Max thickness 2% at 34% chord Max camber 0.5% at 83% chord Max Cl/Cd 40.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s1010-il) S1010 HPV airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1010 HPV airfoil Max thickness 6% at 23.3% chord Max camber 0% at 0% chord Max Cl/Cd 40.1 at Re# 200,000 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 40 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ls013-il) NASA/LANGLEY LS(1)-0013 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0013 general aviation airfoil Max thickness 12.9% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 39.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(oaf139-il) OAF139 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OAF139 Fenestron airfoil Max thickness 13.7% at 23.2% chord Max camber 0% at 0.1% chord Max Cl/Cd 39.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n64012a-il) NACA 64-012A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-012A airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 39.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sc20012-il) NASA SC(2)-0012 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0012 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 0% at 0% chord Max Cl/Cd 39.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database