GOE 494 AIRFOIL (goe494-il)
GOE 494 AIRFOIL - Gottingen 494 airfoil
| Details | Dat file | Parser | |
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(goe494-il) GOE 494 AIRFOIL Gottingen 494 airfoil Max thickness 5% at 20% chord. Max camber 5.1% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 494 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0124200 0.0115900
0.0248800 0.0171700
0.0498200 0.0263500
0.0747600 0.0345200
0.0997200 0.0407000
0.1496500 0.0500500
0.1996000 0.0569000
0.2995300 0.0666000
0.3995000 0.0713000
0.4995100 0.0705000
0.5995400 0.0652000
0.6996200 0.0539000
0.7997200 0.0401000
0.8998500 0.0218000
0.9499199 0.0116500
1.0000000 0.0000000
0.0000000 0.0000000
0.0125500 -.0074100
0.0250500 -.0073200
0.0500400 -.0061500
0.0750300 -.0041700
0.1000200 -.0023000
0.1499900 0.0020500
0.1999500 0.0074000
0.2998700 0.0181000
0.3998100 0.0268000
0.4997800 0.0315000
0.5997700 0.0327000
0.6997899 0.0299000
0.7998400 0.0226000
0.8999100 0.0128000
0.9499400 0.0066600
1.0000000 0.0000000
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Polars for GOE 494 AIRFOIL (goe494-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe494-il | 50,000 | 9 | 44.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 50,000 | 5 | 45.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe494-il | 100,000 | 9 | 69.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 100,000 | 5 | 69.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe494-il | 200,000 | 9 | 97 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 200,000 | 5 | 95.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe494-il | 500,000 | 9 | 135.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 500,000 | 5 | 121.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe494-il | 1,000,000 | 9 | 164.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 1,000,000 | 5 | 112.3 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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