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.

(goe703-il) GOE 703 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 703 airfoil Max thickness 19.4% at 30% chord Max camber 2.3% at 30% chord Source UIUC Airfoil Coordinates Database
(ls417mod-il) NASA/LANGLEY LS(1)-0417MOD 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)-0417MOD general aviation airfoil Max thickness 17% at 30.2% chord Max camber 2.3% at 20.2% chord Source UIUC Airfoil Coordinates Database
(ls421mod-il) NASA/LANGLEY LS(1)-0421MOD 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)-0421MOD general aviation airfoil Max thickness 21% at 32.5% chord Max camber 2.3% at 30% chord 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 Source UIUC Airfoil Coordinates Database
(n5h10-il) NACA 5-H-10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 5-H-10 rotorcraft airfoil Max thickness 9.9% at 40% chord Max camber 2.3% at 40% chord Source UIUC Airfoil Coordinates Database
(oa212-il) ONERA OA212 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OA212 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 12% at 31.8% chord Max camber 2.3% at 31.8% chord Source UIUC Airfoil Coordinates Database
(s3002-il) SELIG 3002-099-83		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3002 low Reynolds number airfoil Max thickness 9.9% at 30.6% chord Max camber 2.3% at 49.8% chord Source UIUC Airfoil Coordinates Database
(s3010-il) S3010-103-84		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3010 low Reynolds number airfoil Max thickness 10.3% at 25% chord Max camber 2.3% at 43.3% chord Source UIUC Airfoil Coordinates Database
(s813-nr) NREL's S813 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S813 tip Max thickness 16% at 40.4% chord Max camber 2.3% at 54.4% chord Source NWTC National WInd Technology Center
(sd7084-il) SD7084 (9.6%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7084 low Reynolds number airfoil Max thickness 9.6% at 29.5% chord Max camber 2.3% at 38.9% chord Source UIUC Airfoil Coordinates Database

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