GOE 655 AIRFOIL (goe655-il)
GOE 655 AIRFOIL - Gottingen 655 airfoil
| Details | Dat file | Parser | |
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(goe655-il) GOE 655 AIRFOIL Gottingen 655 airfoil Max thickness 13.9% at 30% chord. Max camber 4.4% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 655 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0269800
0.0250000 0.0404600
0.0500000 0.0604300
0.0750000 0.0748900
0.1000000 0.0853500
0.1500000 0.0987700
0.2000000 0.1077000
0.3000000 0.1125500
0.4000000 0.1089000
0.5000000 0.0997500
0.6000000 0.0861000
0.7000000 0.0684500
0.8000000 0.0488000
0.9000000 0.0256500
0.9500000 0.0130800
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0140200
0.0250000 -.0190400
0.0500000 -.0240800
0.0750000 -.0271100
0.1000000 -.0291500
0.1500000 -.0307200
0.2000000 -.0303000
0.3000000 -.0264500
0.4000000 -.0211000
0.5000000 -.0157500
0.6000000 -.0114000
0.7000000 -.0075500
0.8000000 -.0042000
0.9000000 -.0018500
0.9500000 -.0009300
1.0000000 0.0000000
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Polars for GOE 655 AIRFOIL (goe655-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe655-il | 50,000 | 9 | 16.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe655-il | 50,000 | 5 | 32.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe655-il | 100,000 | 9 | 45.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe655-il | 100,000 | 5 | 49 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe655-il | 200,000 | 9 | 64.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe655-il | 200,000 | 5 | 64.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe655-il | 500,000 | 9 | 91.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe655-il | 500,000 | 5 | 89.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe655-il | 1,000,000 | 9 | 115.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe655-il | 1,000,000 | 5 | 109 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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