GOE 502 AIRFOIL (goe502-il)
GOE 502 AIRFOIL - Gottingen 502 airfoil
| Details | Dat file | Parser | |
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(goe502-il) GOE 502 AIRFOIL Gottingen 502 airfoil Max thickness 15.9% at 29.3% chord. Max camber 6.1% at 49.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 502 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0110100 0.0295600
0.0228500 0.0426500
0.0469300 0.0608700
0.0712100 0.0751000
0.0956400 0.0863300
0.1447800 0.1033100
0.1941300 0.1163000
0.2933900 0.1308200
0.3932900 0.1328600
0.4936700 0.1254300
0.5943700 0.1115200
0.6954200 0.0906200
0.7966600 0.0662300
0.8982100 0.0353600
0.9490400 0.0189300
1.0000000 0.0000000
0.0000000 0.0000000
0.0137500 -.0248100
0.0266000 -.0316600
0.0518900 -.0373800
0.0771000 -.0416100
0.1021900 -.0433400
0.1521600 -.0428200
0.2019900 -.0393000
0.3013800 -.0272800
0.4007200 -.0142600
0.5001400 -.0027400
0.5997600 0.0047900
0.6995000 0.0098200
0.7994500 0.0108700
0.8996000 0.0079300
0.9496500 0.0043900
1.0000000 0.0000000
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Polars for GOE 502 AIRFOIL (goe502-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe502-il | 50,000 | 9 | 5.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe502-il | 50,000 | 5 | 18.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe502-il | 100,000 | 9 | 42.1 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe502-il | 100,000 | 5 | 53 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe502-il | 200,000 | 9 | 76 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe502-il | 200,000 | 5 | 75.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe502-il | 500,000 | 9 | 106.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe502-il | 500,000 | 5 | 100.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe502-il | 1,000,000 | 9 | 132.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe502-il | 1,000,000 | 5 | 112.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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