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.

(ms317-il) NASA/LANGLEY MS(1)-0317 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley MS(1)-0317 general aviation airfoil Max thickness 17% at 37.5% chord Max camber 1.7% at 72.5% chord Max Cl/Cd 69.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e360-il) EPPLER 360 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E360 rotorcraft airfoil Max thickness 12.2% at 36.9% chord Max camber 1.6% at 27.2% chord Max Cl/Cd 69.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx66h60-il) FX 66-H-60		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-H-60 airfoil Max thickness 6% at 22.2% chord Max camber 1.7% at 17% chord Max Cl/Cd 69.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s102s-il) SOMERS S102 AIRFOIL (SHARP)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dan Somers airfoil for the Toyota general aviation airplane Max thickness 15% at 40% chord Max camber 2.1% at 68.7% chord Max Cl/Cd 69.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(b737b-il) BOEING 737 MIDSPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company model 737 airfoils Max thickness 12.5% at 29.7% chord Max camber 0.8% at 10% chord Max Cl/Cd 69.8 at Re# 500,000 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 69.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ms313-il) NASA/LANGLEY MS(1)-0313 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley MS(1)-0313 general aviation airfoil (buggy Max thickness 13.1% at 37.5% chord Max camber 1.8% at 67.5% chord Max Cl/Cd 69.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(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 69.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(raf26-il) RAF 26 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-26 airfoil Max thickness 6.6% at 29.9% chord Max camber 2.1% at 49.9% chord Max Cl/Cd 69.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(npl9660-il) NPL 9660 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9660 rotorcraft airfoil Max thickness 11.3% at 34.2% chord Max camber 1% at 19.8% chord Max Cl/Cd 69.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database