GOE 626 AIRFOIL (goe626-il)
GOE 626 AIRFOIL - Gottingen 626 airfoil
| Details | Dat file | Parser | |
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(goe626-il) GOE 626 AIRFOIL Gottingen 626 airfoil Max thickness 16.5% at 19.3% chord. Max camber 5.1% at 49.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 626 AIRFOIL
17. 17.
0.0000100 0.0000000
0.0106300 0.0277200
0.0221000 0.0429900
0.0459100 0.0606000
0.0699900 0.0742200
0.0942400 0.0853600
0.1432400 0.1001700
0.1925100 0.1109900
0.2918600 0.1207000
0.3919700 0.1189600
0.4925600 0.1102500
0.5935200 0.0960600
0.6946400 0.0793900
0.7961400 0.0572400
0.8979000 0.0311100
0.9488800 0.0165500
1.0000000 0.0000000
0.0000100 0.0000000
0.0140300 -.0225500
0.0270100 -.0296800
0.0527300 -.0404400
0.0781600 -.0467200
0.1034500 -.0510200
0.1537300 -.0551200
0.2036300 -.0537500
0.3025700 -.0380800
0.4014500 -.0214000
0.5005200 -.0077100
0.5998700 0.0019900
0.6994800 0.0077100
0.7993600 0.0094600
0.8995500 0.0067200
0.9497200 0.0041100
1.0000000 0.0000000
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Polars for GOE 626 AIRFOIL (goe626-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe626-il | 50,000 | 9 | 7.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe626-il | 50,000 | 5 | 30.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe626-il | 100,000 | 9 | 48.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe626-il | 100,000 | 5 | 51.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe626-il | 200,000 | 9 | 71.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe626-il | 200,000 | 5 | 64.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe626-il | 500,000 | 9 | 90.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe626-il | 500,000 | 5 | 82.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe626-il | 1,000,000 | 9 | 107.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe626-il | 1,000,000 | 5 | 94.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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