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.

(goe319-il) GOE 319 (HANSA-BRANDENBURG II) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 319 (Hansa-Brandenburg II) airfoil Max thickness 10.3% at 29.8% chord Max camber 5.8% at 29.8% chord Max Cl/Cd 53.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe363-il) GOE 363 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 363 airfoil Max thickness 11.1% at 19.8% chord Max camber 5.7% at 39.8% chord Max Cl/Cd 53.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sa7035-il) SA7035		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Ashok Gopalarathnam SA7035 Max thickness 9.2% at 27.9% chord Max camber 2.4% at 41.9% chord Max Cl/Cd 53.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s806a-nr) NREL's S806A Airfoil (modified line 35)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S806A tip Max thickness 11.5% at 45% chord Max camber 2.8% at 45% chord Max Cl/Cd 53.3 at Re# 100,000 Source NWTC National WInd Technology Center
(mh18-il) MH 18 11.16%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 18 for F3D Pylon Racing Max thickness 11.1% at 36.8% chord Max camber 2.7% at 42.1% chord Max Cl/Cd 53.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(ls413mod-il) NASA/LANGLEY LS(1)-0413MOD 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)-0413MOD general aviation airfoil Max thickness 13% at 35% chord Max camber 2.2% at 40% chord Max Cl/Cd 53.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe613-il) GOE 613 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 613 airfoil Max thickness 10.3% at 30% chord Max camber 4.1% at 40% chord Max Cl/Cd 53.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(m23-il) NACA M23 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-23 airfoil Max thickness 8.1% at 30.1% chord Max camber 6.4% at 30.1% chord Max Cl/Cd 53.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe532-il) GOE 532 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 532 airfoil Max thickness 12.5% at 30% chord Max camber 4.8% at 40% chord Max Cl/Cd 53.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e207-il) E207 (12.04%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E207 low Reynolds number airfoil Max thickness 12% at 29.6% chord Max camber 2.5% at 38.6% chord Max Cl/Cd 53.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database