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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.

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(goe222-il) GOE 222 (MVA H.33) AIRFOIL

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GOE 222 (MVA H.33) AIRFOILGottingen 222 (MVA H.33) airfoil
Max thickness 18.5% at 29.2% chord
Max camber 7.2% at 49.2% chord
Source UIUC Airfoil Coordinates Database

(goe223-il) GOE 223 (MVA H.34) AIRFOIL

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GOE 223 (MVA H.34) AIRFOILGottingen 223 (MVA H.34) airfoil
Max thickness 18.8% at 29.1% chord
Max camber 5.7% at 49.1% chord
Source UIUC Airfoil Coordinates Database

(goe225-il) GOE 225 (MVA H.35) AIRFOIL

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GOE 225 (MVA H.35) AIRFOILGottingen 225 (MVA H.35) airfoil
Max thickness 12.8% at 19.7% chord
Max camber 7.6% at 49.7% chord
Source UIUC Airfoil Coordinates Database

(goe226-il) GOE 226 (MVA H.36) AIRFOIL

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GOE 226 (MVA H.36) AIRFOILGottingen 226 (MVA H.36) airfoil
Max thickness 13.9% at 19.7% chord
Max camber 8.1% at 49.7% chord
Source UIUC Airfoil Coordinates Database

(goe227-il) GOE 227 (MVA H.37) AIRFOIL

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GOE 227 (MVA H.37) AIRFOILGottingen 227 (MVA H.37) airfoil
Max thickness 14.6% at 25% chord
Max camber 7.8% at 50% chord
Source UIUC Airfoil Coordinates Database

(goe228-il) GOE 228 (MVA H.38) AIRFOIL

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GOE 228 (MVA H.38) AIRFOILGottingen 228 (MVA H.38) airfoil
Max thickness 17.9% at 29.4% chord
Max camber 7% at 49.4% chord
Source UIUC Airfoil Coordinates Database

(goe229-il) GOE 229 (MVA H.39) AIRFOIL

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GOE 229 (MVA H.39) AIRFOILGottingen 229 (MVA H.39) airfoil
Max thickness 19.3% at 29% chord
Max camber 5.9% at 49.1% chord
Source UIUC Airfoil Coordinates Database

(goe233-il) GOE 233 (MVA CA4) AIRFOIL

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GOE 233 (MVA CA4) AIRFOILGottingen 233 (MVA CA4) airfoil
Max thickness 11.6% at 19.8% chord
Max camber 8.2% at 49.8% chord
Source UIUC Airfoil Coordinates Database

(goe234-il) GOE 234 (MVA CA5) AIRFOIL

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GOE 234 (MVA CA5) AIRFOILGottingen 234 (MVA CA5) airfoil
Max thickness 14.2% at 19.7% chord
Max camber 9.2% at 49.7% chord
Source UIUC Airfoil Coordinates Database

(goe235-il) GOE 235 (SCHTTE-LANZ) AIRFOIL

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GOE 235 (SCHTTE-LANZ) AIRFOILGottingen 235 (SCHATTE-LANZ) airfoil
Max thickness 6.5% at 19.9% chord
Max camber 3.5% at 39.9% chord
Source UIUC Airfoil Coordinates Database
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