GOE 55 AIRFOIL (goe55-il)
GOE 55 AIRFOIL - Gottingen 55 airfoil
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(goe55-il) GOE 55 AIRFOIL Gottingen 55 airfoil Max thickness 6.2% at 14.9% chord. Max camber 2% at 19.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 55 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0122300 0.0197700
0.0246500 0.0257400
0.0495200 0.0345800
0.0744400 0.0406200
0.0993900 0.0443700
0.1493300 0.0490500
0.1993000 0.0509400
0.2993700 0.0460200
0.3994600 0.0393900
0.4995500 0.0335600
0.5996200 0.0278400
0.6997000 0.0218200
0.7997700 0.0164000
0.8998500 0.0101800
0.9499000 0.0069600
1.0000000 0.0037500
0.0000000 0.0000000
0.0126800 -.0133300
0.0252200 -.0160500
0.0502300 -.0168100
0.0752200 -.0161700
0.1002000 -.0144200
0.1501700 -.0125400
0.2001400 -.0101500
0.3000900 -.0068700
0.4000600 -.0045000
0.5000400 -.0031200
0.6000200 -.0017500
0.7000100 -.0009700
0.8000100 -.0008000
0.9000200 -.0017200
0.9500400 -.0027400
1.0000000 -.0037500
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Polars for GOE 55 AIRFOIL (goe55-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe55-il | 50,000 | 9 | 26.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe55-il | 50,000 | 5 | 32.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe55-il | 100,000 | 9 | 42.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe55-il | 100,000 | 5 | 43.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe55-il | 200,000 | 9 | 54.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe55-il | 200,000 | 5 | 51.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe55-il | 500,000 | 9 | 64.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe55-il | 500,000 | 5 | 64.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe55-il | 1,000,000 | 9 | 72.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe55-il | 1,000,000 | 5 | 77.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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