Airfoil Tools
Search 1638 airfoils Google+
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.

Optional
Optional
Optional
Optional. Symmetrical airfoils = 0
Optional


(goe184-il) GOE 184 (MVA H.29) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 184 (MVA H.29) AIRFOILGottingen 184 (MVA H.29) airfoil
Max thickness 8.3% at 19.9% chord
Max camber 5.3% at 39.9% chord
Source UIUC Airfoil Coordinates Database

(goe187-il) GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 187 (SCHTTE-LANZ 2U10) AIRFOILGottingen 187 (Schatte-Lanz 2U10) airfoil
Max thickness 8.3% at 30% chord
Max camber 4.8% at 30% chord
Source UIUC Airfoil Coordinates Database

(goe188-il) GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 188 (SCHTTE-LANZ 3U10) AIRFOILGottingen 188 (Schatte-Lanz 3U10) airfoil
Max thickness 8.9% at 30% chord
Max camber 4.3% at 30% chord
Source UIUC Airfoil Coordinates Database

(goe190-il) GOE 190 (MVA MK.18) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 190 (MVA MK.18) AIRFOILGottingen 190 (MVA MK.18) airfoil
Max thickness 12.7% at 19.7% chord
Max camber 5.9% at 49.7% chord
Source UIUC Airfoil Coordinates Database

(goe195-il) GOE 195 AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 195 AIRFOILGottingen 195 airfoil
Max thickness 8.6% at 20% chord
Max camber 5.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(goe198-il) GOE 198 (L.F.G. 5294) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 198 (L.F.G. 5294) AIRFOILGottingen 198 (L.F.G. 5294) airfoil
Max thickness 7.8% at 19.9% chord
Max camber 6.5% at 39.9% chord
Source UIUC Airfoil Coordinates Database

(goe199-il) GOE 199 (L.F.G. 5406) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 199 (L.F.G. 5406) AIRFOILGottingen 199 (L.F.G. 5406) airfoil
Max thickness 7.3% at 30% chord
Max camber 5.2% at 30% chord
Source UIUC Airfoil Coordinates Database

(goe207-il) GOE 207 (AVIATIK V8) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 207 (AVIATIK V8) AIRFOILGottingen 207 (AVIATIK V8) airfoil
Max thickness 8.8% at 19.9% chord
Max camber 6.6% at 29.9% chord
Source UIUC Airfoil Coordinates Database

(goe210-il) GOE 210 (DAIMLER) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 210 (DAIMLER) AIRFOILGottingen 210 (DAIMLER) airfoil
Max thickness 6.6% at 30% chord
Max camber 4.3% at 40% chord
Source UIUC Airfoil Coordinates Database

(goe217-il) GOE 217 (MVA MK.12) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 217 (MVA MK.12) AIRFOILGottingen 217 (MVA MK.12) airfoil
Max thickness 19% at 29.2% chord
Max camber 6.3% at 59.4% chord
Source UIUC Airfoil Coordinates Database
Page 6 of 42     1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20     Next


Please see the source web site or designer for any license conditions.