GOE 115 (MVA MK.2) AIRFOIL (goe115-il)
GOE 115 (MVA MK.2) AIRFOIL - Gottingen 115 (MVA MK.2) airfoil
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(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
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Polars for GOE 115 (MVA MK.2) AIRFOIL (goe115-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe115-il | 50,000 | 9 | 32.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe115-il | 50,000 | 5 | 37.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe115-il | 100,000 | 9 | 57.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe115-il | 100,000 | 5 | 57.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe115-il | 200,000 | 9 | 77.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe115-il | 200,000 | 5 | 76.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe115-il | 500,000 | 9 | 108.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe115-il | 500,000 | 5 | 102.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe115-il | 1,000,000 | 9 | 132 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe115-il | 1,000,000 | 5 | 98.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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