GOE 591 AIRFOIL (goe591-il)
GOE 591 AIRFOIL - Gottingen 591 airfoil
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(goe591-il) GOE 591 AIRFOIL Gottingen 591 airfoil Max thickness 11.2% at 30% chord. Max camber 5.1% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 591 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0217200
0.0250000 0.0334400
0.0500000 0.0498800
0.0750000 0.0628100
0.1000000 0.0722500
0.1500000 0.0866300
0.2000000 0.0960000
0.3000000 0.1052500
0.4000000 0.1045000
0.5000000 0.0972500
0.6000000 0.0850000
0.7000000 0.0682500
0.8000000 0.0480000
0.9000000 0.0257500
0.9500000 0.0131300
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0107800
0.0250000 -.0135600
0.0500000 -.0161200
0.0750000 -.0161900
0.1000000 -.0157500
0.1500000 -.0138800
0.2000000 -.0110000
0.3000000 -.0067500
0.4000000 -.0035000
0.5000000 -.0012500
0.6000000 -.0005000
0.7000000 0.0002500
0.8000000 0.0005000
0.9000000 0.0002500
0.9500000 0.0006300
1.0000000 0.0000000
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Polars for GOE 591 AIRFOIL (goe591-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe591-il | 50,000 | 9 | 16 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe591-il | 50,000 | 5 | 34.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe591-il | 100,000 | 9 | 52.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe591-il | 100,000 | 5 | 57.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe591-il | 200,000 | 9 | 77.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe591-il | 200,000 | 5 | 76.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe591-il | 500,000 | 9 | 108 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe591-il | 500,000 | 5 | 103.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe591-il | 1,000,000 | 9 | 132.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe591-il | 1,000,000 | 5 | 122.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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