GOE 647 AIRFOIL (goe647-il)
GOE 647 AIRFOIL - Gottingen 647 airfoil
| Details | Dat file | Parser | |
|
(goe647-il) GOE 647 AIRFOIL Gottingen 647 airfoil Max thickness 16.2% at 19.5% chord. Max camber 5.3% at 39.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 647 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0111500 0.0314800
0.0229800 0.0469900
0.0470100 0.0695200
0.0713000 0.0860700
0.0957400 0.0991200
0.1449400 0.1177300
0.1945000 0.1278600
0.2942800 0.1331500
0.3944800 0.1284600
0.4949800 0.1167800
0.5957200 0.0996200
0.6966100 0.0789500
0.7976400 0.0548000
0.8987700 0.0286500
0.9493600 0.0148200
1.0000000 0.0000000
0.0000000 0.0000000
0.0132100 -.0164300
0.0259400 -.0218800
0.0512000 -.0278000
0.0763400 -.0312200
0.1014300 -.0331400
0.1515300 -.0354800
0.2014800 -.0343400
0.3012300 -.0285500
0.4009100 -.0212600
0.5006000 -.0139700
0.6004000 -.0091800
0.7002300 -.0053900
0.8001300 -.0030900
0.9000599 -.0013000
0.9500500 -.0011500
1.0000000 0.0000000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GOE 647 AIRFOIL (goe647-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe647-il | 50,000 | 9 | 13.1 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe647-il | 50,000 | 5 | 28.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe647-il | 100,000 | 9 | 41.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe647-il | 100,000 | 5 | 44.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe647-il | 200,000 | 9 | 59 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe647-il | 200,000 | 5 | 58.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe647-il | 500,000 | 9 | 81.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe647-il | 500,000 | 5 | 81.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe647-il | 1,000,000 | 9 | 105.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe647-il | 1,000,000 | 5 | 104.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||