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.

(rae5212-il) RAE(NPL) 5212 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE(NPL) 5212 transonic airfoil Max thickness 11.9% at 35.5% chord Max camber 1.8% at 69.1% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx082512-il) WORTMANN FX 082-512 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 082-512 airfoil Max thickness 11.8% at 25% chord Max camber 4.2% at 62.9% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s8065-il) S8065 (11% version of S8064)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for Q-40 pylon racing (11%). Max thickness 11% at 37.8% chord Max camber 1.1% at 56.3% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca1410-il) NACA 1410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 1410 airfoil Max thickness 10% at 29.9% chord Max camber 1% at 50% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ag10-il) AG10		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG10 airfoil Max thickness 4.7% at 16% chord Max camber 1.7% at 32.1% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(goe92-il) GOE 92 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 92 airfoil Max thickness 8.8% at 30% chord Max camber 5.5% at 30% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(usa40b-il) USA 40 B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-40B airfoil Max thickness 13.6% at 20% chord Max camber 4% at 40% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e209-il) E209 (13.72%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E209 low Reynolds number airfoil Max thickness 13.7% at 33.8% chord Max camber 1.6% at 48.1% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx61140-il) FX 61-140 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 61-140 airfoil Max thickness 14% at 33.9% chord Max camber 2.5% at 30.9% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(eh1090-il) EH 1.0/9.0		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 1.0/9.0 for tailless R/C aircraft Max thickness 9% at 28.7% chord Max camber 1% at 25.9% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database