GOE 412 AIRFOIL (goe412-il)
GOE 412 AIRFOIL - Gottingen 412 airfoil
| Details | Dat file | Parser | |
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(goe412-il) GOE 412 AIRFOIL Gottingen 412 airfoil Max thickness 13.1% at 29.7% chord. Max camber 5.1% at 39.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 412 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0118800 0.0222300
0.0240600 0.0338700
0.0485900 0.0509500
0.0732400 0.0634300
0.0979300 0.0747100
0.1475200 0.0894900
0.1972200 0.1004600
0.2968700 0.1128200
0.3967800 0.1160900
0.4969200 0.1113600
0.5972500 0.0992400
0.6977600 0.0807300
0.7984000 0.0579200
0.8991200 0.0319100
0.9495500 0.0162000
1.0000000 0.0016000
0.0000000 0.0000000
0.0129500 -.0161400
0.0255600 -.0200900
0.0506800 -.0247000
0.0757200 -.0261000
0.1007300 -.0265100
0.1507000 -.0251300
0.2006600 -.0237400
0.3005100 -.0182800
0.4003900 -.0139100
0.5002900 -.0104400
0.6002000 -.0073700
0.7001700 -.0062100
0.8001200 -.0044400
0.9001100 -.0038700
0.9500800 -.0029800
1.0000000 -.0016000
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Polars for GOE 412 AIRFOIL (goe412-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe412-il | 50,000 | 9 | 15.9 at α=15.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe412-il | 50,000 | 5 | 26.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe412-il | 100,000 | 9 | 54.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe412-il | 100,000 | 5 | 55.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe412-il | 200,000 | 9 | 82.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe412-il | 200,000 | 5 | 79.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe412-il | 500,000 | 9 | 116.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe412-il | 500,000 | 5 | 103.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe412-il | 1,000,000 | 9 | 137.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe412-il | 1,000,000 | 5 | 113.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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