GOE 210 (DAIMLER) AIRFOIL (goe210-il)
GOE 210 (DAIMLER) AIRFOIL - Gottingen 210 (DAIMLER) airfoil
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(goe210-il) GOE 210 (DAIMLER) AIRFOIL Gottingen 210 (DAIMLER) airfoil Max thickness 6.6% 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 210 (DAIMLER) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0124100 0.0181600
0.0248600 0.0281200
0.0498000 0.0395500
0.0747600 0.0486700
0.0997200 0.0557000
0.1496800 0.0639500
0.1996500 0.0695000
0.2996200 0.0753000
0.3996200 0.0762000
0.4996400 0.0726000
0.5996800 0.0640000
0.6997400 0.0512000
0.7998200 0.0366000
0.8999000 0.0207000
0.9499500 0.0109500
1.0000000 0.0008000
0.0000000 0.0000000
0.0125300 -.0057400
0.0250300 -.0056000
0.0500200 -.0044500
0.0750100 -.0022700
0.1000000 0.0000000
0.1499800 0.0032500
0.1999700 0.0058000
0.2999600 0.0090000
0.3999500 0.0106600
0.4999400 0.0118000
0.5999400 0.0112000
0.6999600 0.0093900
0.7999600 0.0072000
0.8999800 0.0038000
0.9499900 0.0014500
1.0000000 -.0008000
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Polars for GOE 210 (DAIMLER) AIRFOIL (goe210-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe210-il | 50,000 | 9 | 40.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe210-il | 50,000 | 5 | 43.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe210-il | 100,000 | 9 | 62 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe210-il | 100,000 | 5 | 62 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe210-il | 200,000 | 9 | 82.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe210-il | 200,000 | 5 | 77.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe210-il | 500,000 | 9 | 105.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe210-il | 500,000 | 5 | 86.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe210-il | 1,000,000 | 9 | 116.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe210-il | 1,000,000 | 5 | 99.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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