Airfoil Tools
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Airfoil database search (Symmetrical)

Search the 1636 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.

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(rae101-il) RAE 101 AIRFOIL

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RAE 101 AIRFOILRAE 101 airfoil
Max thickness 10% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(rae100-il) RAE 100 AIRFOIL

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RAE 100 AIRFOILRAE 100 airfoil
Max thickness 10% at 26% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001064-il) NACA 0010-64

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NACA 0010-64NACA 0010-64 airfoil
Max thickness 10% at 40% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001035-il) NACA 0010-35

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NACA 0010-35NACA 0010-35 airfoil
Max thickness 10% at 50% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca0010-il) NACA 0010

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NACA 0010NACA 0010 airfoil
Max thickness 10% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001066-il) NACA 0010-66

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NACA 0010-66NACA 0010-66 airfoil
Max thickness 10% at 60% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(n63010a-il) NACA 63A010 AIRFOIL

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NACA 63A010 AIRFOILNACA 63-010A airfoil
Max thickness 10% at 35% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca64a010-il) NACA 64A-010 10.0%

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NACA 64A-010 10.0%NACA 64A010 airfoil
Max thickness 10% at 40% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001034-il) NACA 0010-34

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NACA 0010-34NACA 0010-34 airfoil
Max thickness 10% at 40% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001065-il) NACA 0010-65

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NACA 0010-65NACA 0010-65 airfoil
Max thickness 10% at 50% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
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