Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 115 (MVA MK.2) AIRFOIL (goe115-il)

GOE 115 (MVA MK.2) AIRFOIL - Gottingen 115 (MVA MK.2) airfoil


Airfoil goe115-il
Details Dat file Parser  
(goe115-il) GOE 115 (MVA MK.2) AIRFOIL
Gottingen 115 (MVA MK.2) airfoil
Max thickness 9.7% at 29.7% chord.
Max camber 3.7% at 39.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 115 (MVA MK.2) AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0120800 0.0130800
 0.0243700 0.0197800
 0.0490400 0.0302600
 0.0737400 0.0395500
 0.0984900 0.0476300
 0.1480800 0.0604100
 0.1977800 0.0698900
 0.2974500 0.0801600
 0.3973500 0.0833400
 0.4975300 0.0775200
 0.5978900 0.0663100
 0.6983300 0.0525100
 0.7988600 0.0360000
 0.8994100 0.0187000
 0.9496900 0.0097000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0128200 -.0101900
 0.0254000 -.0126900
 0.0505700 -.0178900
 0.0756800 -.0213900
 0.1007800 -.0244000
 0.1508100 -.0260300
 0.2008100 -.0254100
 0.3005300 -.0166400
 0.4002700 -.0085700
 0.5001000 -.0032000
 0.5999800 0.0006800
 0.6999199 0.0024600
 0.7999200 0.0026400
 0.8999400 0.0018200
 0.9499900 0.0004100
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 596 AIRFOILPreviewDetails
GOE 602 AIRFOILPreviewDetails
Rhode St. Genese 30PreviewDetails
S4180-098-84PreviewDetails
MH 38 9.68%PreviewDetails
S2091-101-83PreviewDetails
S4061-096-84PreviewDetails
GOE 389 AIRFOILPreviewDetails
AQUILA 9.3% smoothedPreviewDetails
GOE 595 AIRFOILPreviewDetails

Polars for GOE 115 (MVA MK.2) AIRFOIL (goe115-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe115-il50,000932.2 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   goe115-il50,000537.9 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe115-il100,000957.1 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe115-il100,000557.6 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe115-il200,000977.6 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe115-il200,000576.7 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe115-il500,0009108.2 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe115-il500,0005102.9 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   goe115-il1,000,0009132 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   goe115-il1,000,000598.7 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit