GOE 155 (SSW D.1) AIRFOIL (goe155-il)
GOE 155 (SSW D.1) AIRFOIL - Gottingen 155 (SSW D.1) airfoil
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(goe155-il) GOE 155 (SSW D.1) AIRFOIL Gottingen 155 (SSW D.1) airfoil Max thickness 7% at 29.9% chord. Max camber 5.3% at 39.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 155 (SSW D.1) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0123900 0.0171800
0.0248400 0.0250600
0.0497600 0.0384100
0.0746900 0.0490700
0.0996300 0.0586300
0.1495400 0.0722400
0.1995000 0.0796600
0.2994500 0.0869900
0.3994600 0.0865200
0.4994900 0.0815500
0.5995500 0.0714800
0.6996500 0.0563100
0.7997600 0.0387400
0.8998800 0.0192700
0.9499400 0.0095800
1.0000000 0.0020000
0.0000000 0.0000000
0.0125500 -.0082200
0.0250500 -.0075400
0.0500400 -.0057800
0.0750100 -.0023300
0.1000000 0.0000300
0.1499600 0.0064400
0.1999300 0.0117600
0.2998900 0.0167900
0.3998800 0.0191200
0.4998800 0.0191500
0.5998900 0.0175800
0.6999199 0.0127100
0.7999500 0.0078400
0.9000000 0.0001700
0.9500100 -.0012100
1.0000000 -.0020000
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Polars for GOE 155 (SSW D.1) AIRFOIL (goe155-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe155-il | 50,000 | 9 | 40.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 50,000 | 5 | 42.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 100,000 | 9 | 59.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 100,000 | 5 | 61.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 200,000 | 9 | 82.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 200,000 | 5 | 78.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 500,000 | 9 | 107.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 500,000 | 5 | 98.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 1,000,000 | 9 | 123.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 1,000,000 | 5 | 111 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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