GOE 682 AIRFOIL (goe682-il)
GOE 682 AIRFOIL - Gottingen 682 airfoil
| Details | Dat file | Parser | |
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(goe682-il) GOE 682 AIRFOIL Gottingen 682 airfoil Max thickness 10.7% at 30% chord. Max camber 4.3% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 682 AIRFOIL
15. 15.
0.0000000 0.0000000
0.0125000 0.0208100
0.0250000 0.0311200
0.0500000 0.0462500
0.0750000 0.0573800
0.1000000 0.0665000
0.2000000 0.0865000
0.3000000 0.0945000
0.4000000 0.0940000
0.5000000 0.0880000
0.6000000 0.0765000
0.7000000 0.0615000
0.8000000 0.0435000
0.9000000 0.0230000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0141900
0.0250000 -.0183700
0.0500000 -.0212500
0.0750000 -.0221300
0.1000000 -.0225000
0.2000000 -.0180000
0.3000000 -.0120000
0.4000000 -.0075000
0.5000000 -.0045000
0.6000000 -.0015000
0.7000000 0.0000000
0.8000000 0.0010000
0.9000000 0.0010000
1.0000000 0.0000000
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Polars for GOE 682 AIRFOIL (goe682-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe682-il | 50,000 | 9 | 25.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe682-il | 50,000 | 5 | 37.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe682-il | 100,000 | 9 | 55.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe682-il | 100,000 | 5 | 57.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe682-il | 200,000 | 9 | 78.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe682-il | 200,000 | 5 | 75.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe682-il | 500,000 | 9 | 106.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe682-il | 500,000 | 5 | 97.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe682-il | 1,000,000 | 9 | 126.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe682-il | 1,000,000 | 5 | 112.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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