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.

(naca652215-il) NACA 65(2)-215		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(2)-215 airfoil Max thickness 15% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 96.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e326-il) EPPLER 326 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E326 flying wing airfoil Max thickness 12.9% at 33.4% chord Max camber 2.1% at 19.5% chord Max Cl/Cd 96.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe650-il) GOE 650 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 650 airfoil Max thickness 13.4% at 19.5% chord Max camber 4.4% at 49.5% chord Max Cl/Cd 96.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe795sm-il) GOE 795 smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 795 airfoil (smoothed) Max thickness 8% at 30.9% chord Max camber 2.4% at 43.5% chord Max Cl/Cd 96.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe685-il) GOE 685 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 685 airfoil Max thickness 13.1% at 19.6% chord Max camber 4.2% at 49.5% chord Max Cl/Cd 96.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(mh32-il) MH 32 8.7%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 32 for F3E and F3B Max thickness 8.7% at 30.2% chord Max camber 2.3% at 45.7% chord Max Cl/Cd 96.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fxs03182-il) FX S 03-182 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX S 03-182 airfoil Max thickness 18.2% at 40.2% chord Max camber 2.9% at 56.5% chord Max Cl/Cd 96.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(df101-il) DF 101 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	David Fraser DF 101 low Reynolds number airfoil Max thickness 11% at 29.1% chord Max camber 2.3% at 43.5% chord Max Cl/Cd 96.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(rg12a189-il) RG 12A-1.8/9.0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 12A-1.8/9.0 airfoil Max thickness 9% at 34.4% chord Max camber 1.8% at 34.4% chord Max Cl/Cd 96.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(marske7-il) RONCZ LOW DRAG FLYING WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz/Marske-7 low drag flying wing airfoil Max thickness 12.1% at 42.8% chord Max camber 2.8% at 39.1% chord Max Cl/Cd 96.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database