Airfoil Tools
Search 1638 airfoils

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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.

(tempest2-il) HAWKER TEMPEST 61% SEMISPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hawker Tempest 61% semispan airfoil (NPL?) Max thickness 12% at 37.3% chord Max camber 0.9% at 39.3% chord Source UIUC Airfoil Coordinates Database
(rc12b3-il) NASA/LANGLEY RC-12(B)3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-12(B)3 rotorcraft airfoil Max thickness 12% at 38% chord Max camber 2.2% at 34.3% chord Source UIUC Airfoil Coordinates Database
(m6-il) NACA M6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-6 airfoil Max thickness 12% at 30% chord Max camber 2.2% at 30% chord Source UIUC Airfoil Coordinates Database
(vr5-il) BOEING-VERTOL VR-5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-5 rotorcraft airfoil Max thickness 12% at 35% chord Max camber 3.4% at 35% chord Source UIUC Airfoil Coordinates Database
(prandtl-d-root-ns) Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NASA Preliminary Research Aerodynamic Design To Lower Drag (PRANDTL-D) glider root airfoil Max thickness 12% at 30.9% chord Max camber 3.5% at 37.1% chord Source NASA

(sc1012r8-il) SIKORSKY SC1012R8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky SC1012 R8 rotorcraft airfoil Max thickness 12% at 27.8% chord Max camber 2.7% at 21.8% chord Source UIUC Airfoil Coordinates Database
(rc1264c-il) NASA/LANGLEY RC12-64C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley 12-64C rotorcraft airfoil Max thickness 12% at 40% chord Max camber 1% at 35% chord Source UIUC Airfoil Coordinates Database
(naca23012-il) NACA 23012 12%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23012 airfoil Max thickness 12% at 29.8% chord Max camber 1.8% at 12.7% chord Source UIUC Airfoil Coordinates Database
(naca25112-jf) NACA 25112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 25112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 2% at 27.2% chord Source Javafoil generated
(s1210-il) S1210 12%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1210 high lift low Reynolds number airfoil Max thickness 12% at 21.4% chord Max camber 6.7% at 51.1% chord Source UIUC Airfoil Coordinates Database