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.

(clarkz-il) CLARK Z AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK Z airfoil Max thickness 11.8% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 36.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s7055-il) S7055 (10.5%) Flat-Bottomed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S7055 low Reynolds number airfoil Max thickness 10.5% at 31.8% chord Max camber 3.3% at 38.6% chord Max Cl/Cd 36.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e180-il) E180 (8.59%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E180 low Reynolds number airfoil Max thickness 8.6% at 33.5% chord Max camber 2% at 38.1% chord Max Cl/Cd 36.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx80080-il) WORTMANN FX 80-080		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 80-080 airfoil Max thickness 8.1% at 40.2% chord Max camber 2.2% at 50% chord Max Cl/Cd 36.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx84w097-il) FX 84-W-097		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 84-W-097 airfoil for use on wind turbines (W) Max thickness 9.7% at 33.9% chord Max camber 2.8% at 37.1% chord Max Cl/Cd 36.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(mh117-il) MH 117 9.8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 117 for a propeller for ultralight (tip) Max thickness 9.8% at 29.1% chord Max camber 2.7% at 44.6% chord Max Cl/Cd 36.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca4412-il) NACA 4412		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4412 airfoil Max thickness 12% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 36.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(usa50-il) USA 50 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-50 airfoil Max thickness 7% at 30% chord Max camber 2% at 40% chord Max Cl/Cd 36.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq3011-il) HQ 3.0/11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/11 R/C sailplane airfoil Max thickness 11% at 35% chord Max camber 3% at 50% chord Max Cl/Cd 36.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe269-il) GOE 269 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 269 airfoil Max thickness 6.6% at 29.9% chord Max camber 5% at 39.9% chord Max Cl/Cd 36.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database