GOE 628 AIRFOIL (goe628-il)
GOE 628 AIRFOIL - Gottingen 628 airfoil
| Details | Dat file | Parser | |
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(goe628-il) GOE 628 AIRFOIL Gottingen 628 airfoil Max thickness 16.7% at 19.4% chord. Max camber 5.6% at 39.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 628 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0108200 0.0340400
0.0225700 0.0491200
0.0465200 0.0703000
0.0707400 0.0860000
0.0951400 0.0982100
0.1442500 0.1161400
0.1937100 0.1270900
0.2933400 0.1345200
0.3934900 0.1314800
0.4940400 0.1204500
0.5949000 0.1029500
0.6959900 0.0809500
0.7971800 0.0569600
0.8985400 0.0294800
0.9492600 0.0149900
1.0000000 0.0000000
0.0000000 0.0000000
0.0133400 -.0168400
0.0262200 -.0247000
0.0515600 -.0314500
0.0767900 -.0362000
0.1019300 -.0389500
0.1520300 -.0409700
0.2019600 -.0395000
0.3014900 -.0300800
0.4009000 -.0181600
0.5004300 -.0087300
0.6001400 -.0027900
0.6999700 0.0006500
0.7999500 0.0011000
0.8999500 0.0010500
0.9499700 0.0005200
1.0000000 0.0000000
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Polars for GOE 628 AIRFOIL (goe628-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe628-il | 50,000 | 9 | 6.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe628-il | 50,000 | 5 | 27.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe628-il | 100,000 | 9 | 43.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe628-il | 100,000 | 5 | 47.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe628-il | 200,000 | 9 | 64.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe628-il | 200,000 | 5 | 63.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe628-il | 500,000 | 9 | 88.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe628-il | 500,000 | 5 | 84.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe628-il | 1,000,000 | 9 | 111.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe628-il | 1,000,000 | 5 | 107.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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