GOE 503 AIRFOIL (goe503-il)
GOE 503 AIRFOIL - Gottingen 503 airfoil
| Details | Dat file | Parser | |
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(goe503-il) GOE 503 AIRFOIL Gottingen 503 airfoil Max thickness 15.6% at 29.7% chord. Max camber 7% at 39.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 503 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0118500 0.0277800
0.0240000 0.0425600
0.0484800 0.0646400
0.0730600 0.0827200
0.0977100 0.0973000
0.1472400 0.1174600
0.1969200 0.1311300
0.2965900 0.1449700
0.3965900 0.1453200
0.4968200 0.1351800
0.5972300 0.1180300
0.6977700 0.0949000
0.7983800 0.0687600
0.8991200 0.0376300
0.9495300 0.0198100
1.0000000 0.0000000
0.0000000 0.0000000
0.0127600 -.0112000
0.0254000 -.0169000
0.0505200 -.0223100
0.0755800 -.0247200
0.1005900 -.0251400
0.1505500 -.0234600
0.2004500 -.0192900
0.3002600 -.0109400
0.4001300 -.0056000
0.5001400 -.0057500
0.6002200 -.0093900
0.7002600 -.0110400
0.8002000 -.0087000
0.9001300 -.0053500
0.9500600 -.0026700
1.0000000 0.0000000
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Polars for GOE 503 AIRFOIL (goe503-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe503-il | 50,000 | 9 | 4.2 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe503-il | 50,000 | 5 | 15.7 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe503-il | 100,000 | 9 | 32.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe503-il | 100,000 | 5 | 46.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe503-il | 200,000 | 9 | 68.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe503-il | 200,000 | 5 | 67 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe503-il | 500,000 | 9 | 96.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe503-il | 500,000 | 5 | 91.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe503-il | 1,000,000 | 9 | 120.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe503-il | 1,000,000 | 5 | 109.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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