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.

(apex16-il) Apex 16 (normalized using XFOIL date021206)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela Apex 16 low Reynolds number transonic research airfoil Max thickness 12.9% at 38.6% chord Max camber 2.4% at 59.6% chord Source UIUC Airfoil Coordinates Database
(vr11x-il) BOEING-VERTOL VR-11X AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol/NASA/Dadone VR-11X transonic rotorcraft airfoil Max thickness 11% at 40% chord Max camber 2.4% at 25% chord Source UIUC Airfoil Coordinates Database
(fx66h80-il) FX 66-H-80		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-H-80 airfoil Max thickness 8% at 27.9% chord Max camber 2.5% at 25% chord Source UIUC Airfoil Coordinates Database
(s833-nr) NREL's S833 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S833 primary 18.0% Dia=1 to 3 m Re=4.0E+5 Clmax(S)=1.10 Clmax(R)=1.13 High max lift coef Max thickness 18% at 36.3% chord Max camber 2.5% at 78.8% chord Source NWTC National WInd Technology Center
(ag26-il) AG26 Bubble Dancer DLG by Mark Drela		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG26 airfoil used on the Bubble Dancer R/C DLG Max thickness 6.8% at 23.3% chord Max camber 2.5% at 45.5% chord Source UIUC Airfoil Coordinates Database

(doa5-il) DORNIER A-5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dornier A-5 airfoil (reconstruction) (DO 228 wing) Max thickness 16.2% at 40.1% chord Max camber 2.5% at 76% chord Source UIUC Airfoil Coordinates Database
(clarkyh-il) CLARK YH AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK YH airfoil Max thickness 11.9% at 30% chord Max camber 2.5% at 30% chord Source UIUC Airfoil Coordinates Database
(nasasc2-0714-il) SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0714 airfoil (Ref. NASA TP-2890) Max thickness 13.9% at 37% chord Max camber 2.5% at 80% chord Source UIUC Airfoil Coordinates Database
(hq259b-il) HQ 2.5/9 B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.5/9 B R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 2.5% at 55% chord Source UIUC Airfoil Coordinates Database
(n64212ma-il) NACA 64(1)-212 MOD A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA-NASA/AMES/Hicks 63(1)-212 MOD A airfoil Max thickness 12% at 41.2% chord Max camber 2.5% at 21.5% chord Source UIUC Airfoil Coordinates Database