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


(goe238-il) GOE 238 (HANSA-BRANDENBURG) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 238 (HANSA-BRANDENBURG) AIRFOILGottingen 238 (HANSA-BRANDENBURG) airfoil
Max thickness 9.8% at 29.8% chord
Max camber 5.5% at 29.8% chord
Source UIUC Airfoil Coordinates Database

(goe239-il) GOE 239 (MVA H.31) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 239 (MVA H.31) AIRFOILGottingen 239 (MVA H.31) airfoil
Max thickness 11.2% at 19.8% chord
Max camber 6% at 39.8% chord
Source UIUC Airfoil Coordinates Database

(goe240-il) GOE 240 (KOLLER) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 240 (KOLLER) AIRFOILGottingen 240 (KOLLER) airfoil
Max thickness 7% at 29.9% chord
Max camber 5.2% at 39.9% chord
Source UIUC Airfoil Coordinates Database

(goe241-il) GOE 241 (MVA PR.1) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 241 (MVA PR.1) AIRFOILGottingen 241 (MVA PR.1) airfoil
Max thickness 18.9% at 29.5% chord
Max camber 8.4% at 49.5% chord
Source UIUC Airfoil Coordinates Database

(goe242-il) GOE 242 (MVA PR.2) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 242 (MVA PR.2) AIRFOILGottingen 242 (MVA PR.2) airfoil
Max thickness 16.2% at 29.6% chord
Max camber 7.5% at 49.7% chord
Source UIUC Airfoil Coordinates Database

(goe243-il) GOE 243 (MVA PR.3) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 243 (MVA PR.3) AIRFOILGottingen 243 (MVA PR.3) airfoil
Max thickness 19% at 29.3% chord
Max camber 8.4% at 59.4% chord
Source UIUC Airfoil Coordinates Database

(goe244-il) GOE 244 (MVA PR.4) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 244 (MVA PR.4) AIRFOILGottingen 244 (MVA PR.4) airfoil
Max thickness 17.7% at 19.6% chord
Max camber 10% at 49.6% chord
Source UIUC Airfoil Coordinates Database

(goe255-il) GOE 255 (MVA CA.6) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 255 (MVA CA.6) AIRFOILGottingen 255 (MVA CA.6) airfoil
Max thickness 18.5% at 29.1% chord
Max camber 4.8% at 49.1% chord
Source UIUC Airfoil Coordinates Database

(goe256-il) GOE 256 (JUNKERS E) AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 256 (JUNKERS E) AIRFOILGottingen 256 (JUNKERS E) airfoil
Max thickness 16% at 29.6% chord
Max camber 4.7% at 39.6% chord
Source UIUC Airfoil Coordinates Database

(goe257-il) GOE 257 AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 257 AIRFOILGottingen 257 airfoil
Max thickness 8.8% at 30% chord
Max camber 4.1% at 30% chord
Source UIUC Airfoil Coordinates Database
Page 8 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.