GOE 511 AIRFOIL (goe511-il)
GOE 511 AIRFOIL - Gottingen 511 airfoil
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(goe511-il) GOE 511 AIRFOIL Gottingen 511 airfoil Max thickness 16.6% at 19.9% chord. Max camber 8% at 29.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 511 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0121000 0.0426100
0.0244200 0.0607300
0.0491800 0.0864700
0.0740000 0.1057000
0.0988600 0.1199400
0.1486700 0.1399100
0.1985400 0.1533900
0.2984600 0.1623400
0.3985000 0.1577900
0.4986300 0.1447400
0.5987900 0.1276900
0.6990000 0.1056400
0.7992401 0.0795900
0.8995900 0.0435500
0.9497899 0.0225200
1.0000000 0.0000000
0.0000000 0.0000000
0.0126200 -.0123800
0.0251500 -.0157600
0.0501700 -.0180200
0.0751800 -.0192900
0.1001800 -.0190500
0.1501700 -.0175700
0.2001200 -.0126000
0.3000300 -.0026500
0.3999900 0.0008000
0.5000300 -.0032500
0.6001100 -.0113000
0.7001200 -.0128500
0.8001200 -.0124000
0.9000900 -.0089500
0.9500500 -.0054700
1.0000000 0.0000000
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Polars for GOE 511 AIRFOIL (goe511-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe511-il | 50,000 | 9 | 3.7 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe511-il | 50,000 | 5 | 25.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe511-il | 100,000 | 9 | 41.4 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe511-il | 100,000 | 5 | 41.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe511-il | 200,000 | 9 | 57.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe511-il | 200,000 | 5 | 53.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe511-il | 500,000 | 9 | 71.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe511-il | 500,000 | 5 | 67 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe511-il | 1,000,000 | 9 | 87.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe511-il | 1,000,000 | 5 | 80.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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