GOE 493 AIRFOIL (goe493-il)
GOE 493 AIRFOIL - Gottingen 493 airfoil
| Details | Dat file | Parser | |
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(goe493-il) GOE 493 AIRFOIL Gottingen 493 airfoil Max thickness 14.9% at 29.3% chord. Max camber 3.4% at 49.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 493 AIRFOIL
17. 17.
0.0000100 0.0000000
0.0110100 0.0212800
0.0228800 0.0301100
0.0469200 0.0438100
0.0711600 0.0545200
0.0955100 0.0637300
0.1444900 0.0781900
0.1936800 0.0896500
0.2928000 0.1021400
0.3925200 0.1061700
0.4928000 0.1022400
0.5935300 0.0918400
0.6946499 0.0759700
0.7961500 0.0546300
0.8979700 0.0288100
0.9489500 0.0149000
1.0000000 0.0000000
0.0000100 0.0000000
0.0136000 -.0155400
0.0266000 -.0226200
0.0522500 -.0318200
0.0776500 -.0375300
0.1029100 -.0412400
0.1532300 -.0457000
0.2033700 -.0476600
0.3033300 -.0471200
0.4029700 -.0420900
0.5024100 -.0340800
0.6017700 -.0250800
0.7011700 -.0165700
0.8006000 -.0085600
0.9002100 -.0030300
0.9500000 -.0013300
1.0000000 0.0000000
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Polars for GOE 493 AIRFOIL (goe493-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe493-il | 50,000 | 9 | 24.2 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe493-il | 50,000 | 5 | 24.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe493-il | 100,000 | 9 | 51.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe493-il | 100,000 | 5 | 51.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe493-il | 200,000 | 9 | 75.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe493-il | 200,000 | 5 | 72.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe493-il | 500,000 | 9 | 105.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe493-il | 500,000 | 5 | 95.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe493-il | 1,000,000 | 9 | 127.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe493-il | 1,000,000 | 5 | 98.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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