GOE 676 (= M 12) AIRFOIL (goe676-il)
GOE 676 (= M 12) AIRFOIL - Gottingen 676 (= M 12) airfoil
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(goe676-il) GOE 676 (= M 12) AIRFOIL Gottingen 676 (= M 12) airfoil Max thickness 11.9% at 30% chord. Max camber 2% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 676 (= M 12) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0186200
0.0250000 0.0270400
0.0500000 0.0395700
0.0750000 0.0486100
0.1000000 0.0551500
0.1500000 0.0662200
0.2000000 0.0738000
0.3000000 0.0799500
0.4000000 0.0791000
0.5000000 0.0732500
0.6000000 0.0629000
0.7000000 0.0505500
0.8000000 0.0352000
0.9000000 0.0193500
0.9500000 0.0109200
1.0000000 0.0030000
0.0000000 0.0000000
0.0125000 -.0159800
0.0250000 -.0214600
0.0500000 -.0269300
0.0750000 -.0298900
0.1000000 -.0323500
0.1500000 -.0347700
0.2000000 -.0367000
0.3000000 -.0390500
0.4000000 -.0389000
0.5000000 -.0367500
0.6000000 -.0336000
0.7000000 -.0284500
0.8000000 -.0213000
0.9000000 -.0111500
0.9500000 -.0055800
1.0000000 0.0000000
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Similar airfoils
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Polars for GOE 676 (= M 12) AIRFOIL (goe676-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe676-il | 50,000 | 9 | 30.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe676-il | 50,000 | 5 | 33.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe676-il | 100,000 | 9 | 48.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe676-il | 100,000 | 5 | 48.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe676-il | 200,000 | 9 | 65.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe676-il | 200,000 | 5 | 62.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe676-il | 500,000 | 9 | 86.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe676-il | 500,000 | 5 | 77.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe676-il | 1,000,000 | 9 | 97.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe676-il | 1,000,000 | 5 | 85.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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