GOE 500 AIRFOIL (goe500-il)
GOE 500 AIRFOIL - Gottingen 500 airfoil
| Details | Dat file | Parser | |
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(goe500-il) GOE 500 AIRFOIL Gottingen 500 airfoil Max thickness 10% at 30% chord. Max camber 6% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 500 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0212600
0.0250000 0.0300100
0.0500000 0.0435200
0.0750000 0.0545400
0.1000000 0.0635500
0.1500000 0.0780700
0.2000000 0.0886000
0.3000000 0.1016500
0.4000000 0.1042000
0.5000000 0.1003500
0.6000000 0.0903000
0.7000000 0.0748500
0.8000000 0.0544000
0.9000000 0.0279500
0.9500000 0.0139800
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0117400
0.0250000 -.0154900
0.0500000 -.0184700
0.0750000 -.0189600
0.1000000 -.0174500
0.1500000 -.0139300
0.2000000 -.0094000
0.3000000 0.0016500
0.4000000 0.0117000
0.5000000 0.0197500
0.6000000 0.0248000
0.7000000 0.0253500
0.8000000 0.0204000
0.9000000 0.0124500
0.9500000 0.0064700
1.0000000 0.0000000
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Similar airfoils
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Polars for GOE 500 AIRFOIL (goe500-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe500-il | 50,000 | 9 | 35.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe500-il | 50,000 | 5 | 36.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe500-il | 100,000 | 9 | 64.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe500-il | 100,000 | 5 | 65.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe500-il | 200,000 | 9 | 92 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe500-il | 200,000 | 5 | 91.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe500-il | 500,000 | 9 | 131.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe500-il | 500,000 | 5 | 120.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe500-il | 1,000,000 | 9 | 159.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe500-il | 1,000,000 | 5 | 120.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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