GOE 392 AIRFOIL (goe392-il)
GOE 392 AIRFOIL - Gottingen 392 airfoil
| Details | Dat file | Parser | |
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(goe392-il) GOE 392 AIRFOIL Gottingen 392 airfoil Max thickness 10.2% at 30% chord. Max camber 4.8% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 392 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0111700
0.0250000 0.0188500
0.0500000 0.0332000
0.0750000 0.0445500
0.1000000 0.0544000
0.1500000 0.0706000
0.2000000 0.0828000
0.3000000 0.0947000
0.4000000 0.0966000
0.5000000 0.0910000
0.6000000 0.0804000
0.7000000 0.0653000
0.8000000 0.0472000
0.9000000 0.0271000
0.9500000 0.0148000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0053300
0.0250000 -.0066500
0.0500000 -.0088000
0.0750000 -.0104500
0.1000000 -.0111000
0.1500000 -.0119000
0.2000000 -.0112000
0.3000000 -.0068000
0.4000000 0.0001000
0.5000000 0.0038000
0.6000000 0.0059000
0.7000000 0.0078000
0.8000000 0.0072000
0.9000000 0.0051000
0.9500000 0.0023000
1.0000000 0.0000000
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Polars for GOE 392 AIRFOIL (goe392-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe392-il | 50,000 | 9 | 37.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe392-il | 50,000 | 5 | 38.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe392-il | 100,000 | 9 | 59.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe392-il | 100,000 | 5 | 58.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe392-il | 200,000 | 9 | 78.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe392-il | 200,000 | 5 | 77.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe392-il | 500,000 | 9 | 105.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe392-il | 500,000 | 5 | 102.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe392-il | 1,000,000 | 9 | 125.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe392-il | 1,000,000 | 5 | 120.6 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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