GOE 681 AIRFOIL (goe681-il)
GOE 681 AIRFOIL - Gottingen 681 airfoil
| Details | Dat file | Parser | |
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(goe681-il) GOE 681 AIRFOIL Gottingen 681 airfoil Max thickness 16.8% at 29.2% chord. Max camber 4.4% at 39.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 681 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0106200 0.0301600
0.0223200 0.0428900
0.0460100 0.0638800
0.0700400 0.0793800
0.0942600 0.0918900
0.1431600 0.1094500
0.1925600 0.1190300
0.2921400 0.1257600
0.3922500 0.1240200
0.4928300 0.1148000
0.5938100 0.0991100
0.6951000 0.0784400
0.7966101 0.0542900
0.8982100 0.0286400
0.9490700 0.0148200
1.0000000 0.0000000
0.0000000 0.0000000
0.0140700 -.0251200
0.0269600 -.0313200
0.0524600 -.0392200
0.0777300 -.0436400
0.1029100 -.0465700
0.1530600 -.0489300
0.2029600 -.0473200
0.3026300 -.0420900
0.4022700 -.0363600
0.5018900 -.0301300
0.6015300 -.0244000
0.7011700 -.0186800
0.8007801 -.0124500
0.9003900 -.0062300
0.9501899 -.0031100
1.0000000 0.0000000
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Polars for GOE 681 AIRFOIL (goe681-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe681-il | 50,000 | 9 | 9.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe681-il | 50,000 | 5 | 26.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe681-il | 100,000 | 9 | 44.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe681-il | 100,000 | 5 | 42.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe681-il | 200,000 | 9 | 61.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe681-il | 200,000 | 5 | 55.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe681-il | 500,000 | 9 | 79.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe681-il | 500,000 | 5 | 73.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe681-il | 1,000,000 | 9 | 97.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe681-il | 1,000,000 | 5 | 94 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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