GOE 16K AIRFOIL (goe16k-il)
GOE 16K AIRFOIL - Gottingen 16K airfoil
| Details | Dat file | Parser | |
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(goe16k-il) GOE 16K AIRFOIL Gottingen 16K airfoil Max thickness 18.2% at 50% chord. Max camber 4.1% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 16K AIRFOIL
15. 15.
0.0000000 0.0000000
0.0250000 0.0359200
0.0500000 0.0515500
0.1000000 0.0727000
0.1500000 0.0879500
0.2000000 0.1001000
0.3000000 0.1174000
0.4000000 0.1268000
0.5000000 0.1316000
0.6000000 0.1286000
0.7000000 0.1173000
0.8000000 0.0925000
0.9000000 0.0574000
0.9500000 0.0341500
1.0000000 0.0000000
0.0000000 0.0000000
0.0250000 -.0266800
0.0500000 -.0352500
0.1000000 -.0452000
0.1500000 -.0507500
0.2000000 -.0533000
0.3000000 -.0541000
0.4000000 -.0520000
0.5000000 -.0499000
0.6000000 -.0478000
0.7000000 -.0448000
0.8000000 -.0396000
0.9000000 -.0295000
0.9500000 -.0203500
1.0000000 0.0000000
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Polars for GOE 16K AIRFOIL (goe16k-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe16k-il | 50,000 | 9 | 21.5 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 50,000 | 5 | 16.6 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe16k-il | 100,000 | 9 | 26.4 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 100,000 | 5 | 23.7 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe16k-il | 200,000 | 9 | 35.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 500,000 | 9 | 69.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 500,000 | 5 | 50.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe16k-il | 1,000,000 | 9 | 80.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 1,000,000 | 5 | 70.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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