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.

(goe484-il) GOE 484 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 484 airfoil Max thickness 6.3% at 30% chord Max camber 5% at 50% chord Source UIUC Airfoil Coordinates Database
(e62-il) E62 (5.62%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E62 low Reynolds number airfoil Max thickness 5.6% at 26.2% chord Max camber 5% at 49.3% chord Source UIUC Airfoil Coordinates Database
(goe404-il) GOE 404 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 404 airfoil Max thickness 13.2% at 29.6% chord Max camber 5% at 29.6% chord Source UIUC Airfoil Coordinates Database
(goe584-il) GOE 584 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 584 airfoil Max thickness 12.7% at 30% chord Max camber 5% at 40% chord Source UIUC Airfoil Coordinates Database
(s831-nr) NREL's S831 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S831 tip 18.0% Dia=40 to 50 m Re=3.5E+6 Clmax(S)=1.50 Clmax(R)=1.48 High max lift coef Max thickness 18% at 44.2% chord Max camber 5% at 53.1% chord Source NWTC National WInd Technology Center
(goe308-il) GOE 308 (MVA H.40) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 308 (MVA H.40) airfoil Max thickness 8.1% at 29.9% chord Max camber 5% at 29.9% chord Source UIUC Airfoil Coordinates Database
(goe621-il) GOE 621 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 621 airfoil Max thickness 15% at 29.5% chord Max camber 5% at 49.5% chord Source UIUC Airfoil Coordinates Database
(goe692-il) GOE 692 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 692 airfoil Max thickness 16.1% at 30% chord Max camber 5% at 40% chord Source UIUC Airfoil Coordinates Database
(arad6-il) ARA-D 6% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 6% thick propeller airfoil Max thickness 6% at 20% chord Max camber 5% at 45% chord Source UIUC Airfoil Coordinates Database
(hs1708-il) HAM-STD HS1-708 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 7.9% at 22% chord Max camber 5% at 46% chord Source UIUC Airfoil Coordinates Database

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