GOE 561 AIRFOIL (goe561-il)
GOE 561 AIRFOIL - Gottingen 561 airfoil
| Details | Dat file | Parser | |
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(goe561-il) GOE 561 AIRFOIL Gottingen 561 airfoil Max thickness 25% at 29.8% chord. Max camber 10.2% at 29.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 561 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0120500 0.0501100
0.0243300 0.0742200
0.0490000 0.1110400
0.0737500 0.1391600
0.0985700 0.1588900
0.1482800 0.1913300
0.1980900 0.2117800
0.2979600 0.2271800
0.3980100 0.2215800
0.4982000 0.1994800
0.5984700 0.1698900
0.6987000 0.1334200
0.7991500 0.0946900
0.8993599 0.0520000
0.9497300 0.0300500
1.0000000 0.0000000
0.0000000 0.0000000
0.0126900 -.0213900
0.0252200 -.0242700
0.0502200 -.0240500
0.0752100 -.0238200
0.1002100 -.0236000
0.1502100 -.0231500
0.2002100 -.0232000
0.3002000 -.0223000
0.4001900 -.0214000
0.5001800 -.0205000
0.6001800 -.0196000
0.7001500 -.0172000
0.8001300 -.0148000
0.9001100 -.0124000
0.9500901 -.0104500
1.0000000 0.0000000
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Polars for GOE 561 AIRFOIL (goe561-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe561-il | 50,000 | 9 | 3.3 at α=-13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe561-il | 50,000 | 5 | 5.7 at α=-8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe561-il | 100,000 | 9 | 8.4 at α=-8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe561-il | 100,000 | 5 | 8.6 at α=-6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe561-il | 200,000 | 9 | 28.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe561-il | 200,000 | 5 | 20.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe561-il | 500,000 | 9 | 43.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe561-il | 500,000 | 5 | 33 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe561-il | 1,000,000 | 9 | 49.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe561-il | 1,000,000 | 5 | 42 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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