GOE 650 AIRFOIL (goe650-il)
GOE 650 AIRFOIL - Gottingen 650 airfoil
| Details | Dat file | Parser | |
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(goe650-il) GOE 650 AIRFOIL Gottingen 650 airfoil Max thickness 13.4% at 19.5% chord. Max camber 4.4% at 49.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 650 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0112400 0.0250700
0.0232000 0.0356700
0.0473600 0.0523900
0.0717600 0.0641200
0.0963200 0.0728600
0.1456900 0.0853600
0.1952900 0.0933600
0.2948800 0.1013900
0.3948000 0.1029400
0.4950500 0.0980000
0.5955300 0.0885700
0.6963300 0.0726600
0.7973400 0.0527700
0.8985400 0.0288800
0.9492199 0.0154400
1.0000000 0.0000000
0.0000000 0.0000000
0.0134800 -.0193200
0.0263200 -.0261700
0.0517600 -.0348900
0.0770000 -.0396100
0.1021100 -.0418400
0.1521400 -.0423200
0.2020400 -.0403000
0.3016100 -.0317700
0.4010200 -.0202500
0.5004700 -.0092300
0.6000400 -.0007000
0.6997800 0.0043400
0.7997500 0.0048900
0.8999000 0.0019500
0.9499800 0.0004700
1.0000000 0.0000000
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Polars for GOE 650 AIRFOIL (goe650-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe650-il | 50,000 | 9 | 31.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe650-il | 50,000 | 5 | 34.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe650-il | 100,000 | 9 | 56 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe650-il | 100,000 | 5 | 53.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe650-il | 200,000 | 9 | 79 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe650-il | 200,000 | 5 | 70.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe650-il | 500,000 | 9 | 101.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe650-il | 500,000 | 5 | 83.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe650-il | 1,000,000 | 9 | 109.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe650-il | 1,000,000 | 5 | 96.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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