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.

(nn7mk20-il) NN7 MK20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NN7 MK20 airfoil Max thickness 16.9% at 37.1% chord Max camber 3% at 59.8% chord Source UIUC Airfoil Coordinates Database
(r1082t-il) RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1082T Voyager tip outer aft wing airfoil Max thickness 16% at 40% chord Max camber 3% at 40% chord Source UIUC Airfoil Coordinates Database
(s3024-il) AIRFOIL 3024 9.84%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3024 low Reynolds number airfoil Max thickness 9.8% at 30.7% chord Max camber 3% at 44.7% chord Source UIUC Airfoil Coordinates Database
(s3025-il) S3025 9.38%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3025 low Reynolds number airfoil Max thickness 9.4% at 30.9% chord Max camber 3% at 44.9% chord Source UIUC Airfoil Coordinates Database
(s4053-il) S4053		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4053 low Reynolds number airfoil Max thickness 8.9% at 30.9% chord Max camber 3% at 45% chord Source UIUC Airfoil Coordinates Database
(s814-nr) NREL's S814 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S814 root 24.0% Dia=20 to 30 m Re=1.5E+6 Clmax(S)=1.56 Clmax(R)=1.51 High max lift coef Max thickness 24.1% at 28.4% chord Max camber 3% at 74.5% chord Source NWTC National WInd Technology Center
(sa7038-il) SA7038		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Ashok Gopalarathnam SA7038 Max thickness 9.2% at 28.5% chord Max camber 3% at 42.5% chord Source UIUC Airfoil Coordinates Database
(sm701-il) SM701		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Somers / Maughmer SM701 airfoil Max thickness 16% at 36.3% chord Max camber 3% at 60.3% chord Source UIUC Airfoil Coordinates Database
(ua79sfm-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Alberta/Marsden UA 79-SF-187 sailplane airfoil MAIN ELEMENT Max thickness 18.8% at 42.8% chord Max camber 3% at 66.9% chord Source UIUC Airfoil Coordinates Database
(vr7b-il) BOEING-VERTOL VR-7 AIRFOIL WITH TAB		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-7 rotorcraft airfoil with tab Max thickness 12% at 33% chord Max camber 3% at 29% chord Source UIUC Airfoil Coordinates Database

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