GOE 673 AIRFOIL (goe673-il)
GOE 673 AIRFOIL - Gottingen 673 airfoil
| Details | Dat file | Parser | |
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(goe673-il) GOE 673 AIRFOIL Gottingen 673 airfoil Max thickness 10.8% at 29.7% chord. Max camber 2.8% at 49.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 673 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0119700 0.0129800
0.0241900 0.0199800
0.0487500 0.0309700
0.0733800 0.0399700
0.0980600 0.0479700
0.1475500 0.0604800
0.1972100 0.0689900
0.2968200 0.0785200
0.3967400 0.0805700
0.4968800 0.0771200
0.5972000 0.0691900
0.6976600 0.0577600
0.7982900 0.0423300
0.8990500 0.0234100
0.9494800 0.0129500
1.0000000 0.0020000
0.0000000 0.0000000
0.0128400 -.0084800
0.0255100 -.0124700
0.0507500 -.0184400
0.0759100 -.0224300
0.1010300 -.0254100
0.1511500 -.0283800
0.2012100 -.0298500
0.3011900 -.0293000
0.4010600 -.0262600
0.5008800 -.0217100
0.6007000 -.0171700
0.7004700 -.0116300
0.8002900 -.0070900
0.9001600 -.0040400
0.9501000 -.0025200
1.0000000 -.0020000
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Polars for GOE 673 AIRFOIL (goe673-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe673-il | 50,000 | 9 | 38.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe673-il | 50,000 | 5 | 37.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe673-il | 100,000 | 9 | 56 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe673-il | 100,000 | 5 | 55.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe673-il | 200,000 | 9 | 75 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe673-il | 200,000 | 5 | 73.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe673-il | 500,000 | 9 | 100.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe673-il | 500,000 | 5 | 94.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe673-il | 1,000,000 | 9 | 118.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe673-il | 1,000,000 | 5 | 109.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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