GOE 620 AIRFOIL (goe620-il)
GOE 620 AIRFOIL - Gottingen 620 airfoil
| Details | Dat file | Parser | |
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(goe620-il) GOE 620 AIRFOIL Gottingen 620 airfoil Max thickness 17.5% at 30% chord. Max camber 5.9% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 620 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0321400
0.0250000 0.0482900
0.0500000 0.0700800
0.0750000 0.0858600
0.1000000 0.0971500
0.1500000 0.1162300
0.2000000 0.1283000
0.3000000 0.1409500
0.4000000 0.1421000
0.5000000 0.1342500
0.6000000 0.1189000
0.7000000 0.0955500
0.8000000 0.0677000
0.9000000 0.0358500
0.9500000 0.0184200
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0208600
0.0250000 -.0282100
0.0500000 -.0349300
0.0750000 -.0391400
0.1000000 -.0413500
0.1500000 -.0427800
0.2000000 -.0412000
0.3000000 -.0340500
0.4000000 -.0249000
0.5000000 -.0162500
0.6000000 -.0086000
0.7000000 -.0034500
0.8000000 -.0008000
0.9000000 -.0006500
0.9500000 -.0005800
1.0000000 0.0000000
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Polars for GOE 620 AIRFOIL (goe620-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe620-il | 50,000 | 9 | 4.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 50,000 | 5 | 14.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe620-il | 100,000 | 9 | 42.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 100,000 | 5 | 43.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe620-il | 200,000 | 9 | 71.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 200,000 | 5 | 64.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe620-il | 500,000 | 9 | 97.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 500,000 | 5 | 82.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe620-il | 1,000,000 | 9 | 117.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 1,000,000 | 5 | 87.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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