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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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(naca633018-il) NACA 63(3)-018

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NACA 63(3)-018NACA 63(3)-018 airfoil
Max thickness 18% at 33.9% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca66-018-il) NACA 66-018

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NACA 66-018NACA 66-018 airfoil
Max thickness 18% at 45% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca0018-il) NACA 0018

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NACA 0018NACA 0018 airfoil
Max thickness 18% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(e838-il) EPPLER E838 HYDROFOIL AIRFOIL

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EPPLER E838 HYDROFOIL AIRFOILEppler E838 hydrofoil
Max thickness 18.4% at 37.2% chord
Max camber 0% at 46.5% chord
Source UIUC Airfoil Coordinates Database

(us1000root-il) US1000ROOT

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US1000ROOTGreat Planes R/C Ultra-Sport 1000 airfoil
Max thickness 18.6% at 27.1% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(goe460-il) GOE 460 AIRFOIL

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GOE 460 AIRFOILGottingen 460 airfoil
Max thickness 20.5% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca16021-il) NACA 16-021

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NACA 16-021NACA 16-021 airfoil
Max thickness 21% at 50% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(joukowsk0021-jf) Joukovsky f=0% t=21%

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Joukovsky f=0% t=21%Joukowski 21% symmetrical airfoil
Max thickness 21% at 26.6% chord
Max camber 0% at 0% chord
Source Javafoil generated

(naca0021-il) NACA 0021

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NACA 0021NACA 0021 airfoil
Max thickness 21% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(goe775-il) GOE 775 AIRFOIL

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GOE 775 AIRFOILGottingen 775 airfoil
Max thickness 21% at 30% chord
Max camber 0% at 1.3% chord
Source UIUC Airfoil Coordinates Database
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