Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(fx60160-il) FX 60-160 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-160 airfoil Max thickness 15.6% at 40% chord Max camber 3.1% at 60% chord Source UIUC Airfoil Coordinates Database
(fx61184-il) FX 61-184 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 61-184 airfoil Max thickness 18.4% at 37.1% chord Max camber 3.1% at 62.9% chord Source UIUC Airfoil Coordinates Database
(fx63143-il) FX 63-143 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-143 airfoil Max thickness 14.3% at 33.9% chord Max camber 3.1% at 30.9% chord Source UIUC Airfoil Coordinates Database
(fx63147-il) FX 63-147 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-147 airfoil Max thickness 14.7% at 33.9% chord Max camber 3.1% at 33.9% chord Source UIUC Airfoil Coordinates Database
(goe06k-il) GOE 6K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 6K airfoil Max thickness 7.5% at 50% chord Max camber 3.1% at 50% chord Source UIUC Airfoil Coordinates Database

(hs1404-il) HAM-STD HS1-404 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	HS1 family of prop airfoils from US Patent No. 4 Max thickness 4% at 18% chord Max camber 3.1% at 46% chord Source UIUC Airfoil Coordinates Database
(s4110-il) S4110		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4110 low Reynolds number airfoil Max thickness 8.4% at 26.6% chord Max camber 3.1% at 45.4% chord Source UIUC Airfoil Coordinates Database
(sg6050-il) SG6050		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Giguere SG6050 wind turbine airfoil Max thickness 16% at 31.5% chord Max camber 3.1% at 48.9% chord Source UIUC Airfoil Coordinates Database
(sg6051-il) SG6051		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Giguere SG6051 wind turbine airfoil Max thickness 12% at 35.7% chord Max camber 3.1% at 49.9% chord Source UIUC Airfoil Coordinates Database
(tsagi-r-3a-il) TsAGI R-3a (12%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	TsAGI R-3a used on Russian ultra light aircraft (12%). Max thickness 12.1% at 23.1% chord Max camber 3.1% at 24.1% chord Source UIUC Airfoil Coordinates Database