GOE 614 AIRFOIL (goe614-il)
GOE 614 AIRFOIL - Gottingen 614 airfoil
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(goe614-il) GOE 614 AIRFOIL Gottingen 614 airfoil Max thickness 18.8% at 29.2% chord. Max camber 6.2% at 39.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 614 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0109700 0.0285900
0.0226100 0.0447100
0.0462900 0.0694800
0.0702800 0.0882600
0.0946000 0.1010600
0.1433900 0.1236700
0.1926300 0.1378100
0.2918900 0.1516200
0.3919500 0.1504700
0.4925500 0.1393500
0.5934900 0.1217500
0.6947200 0.0986700
0.7962200 0.0706000
0.8979400 0.0385400
0.9489200 0.0202700
1.0000000 0.0000000
0.0000000 0.0000000
0.0136400 -.0212700
0.0230900 -.0253100
0.0518600 -.0347300
0.0771400 -.0398700
0.1022500 -.0420300
0.1523700 -.0443500
0.2022800 -.0426800
0.3018900 -.0353500
0.4013900 -.0260300
0.5008900 -.0167000
0.6004800 -.0088700
0.7001899 -.0035400
0.8000100 -.0002000
0.9005300 -.0006500
0.9499800 0.0003200
1.0000000 0.0000000
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Polars for GOE 614 AIRFOIL (goe614-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe614-il | 50,000 | 9 | 3.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe614-il | 50,000 | 5 | 16.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe614-il | 100,000 | 9 | 33.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe614-il | 100,000 | 5 | 43.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe614-il | 200,000 | 9 | 63.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe614-il | 200,000 | 5 | 59.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe614-il | 500,000 | 9 | 84.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe614-il | 500,000 | 5 | 77.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe614-il | 1,000,000 | 9 | 105.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe614-il | 1,000,000 | 5 | 79.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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