GOE 451 AIRFOIL (modified line 6) (goe451-il)
GOE 451 AIRFOIL (modified line 6) - Gottingen 451 airfoil
| Details | Dat file | Parser | |
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(goe451-il) GOE 451 AIRFOIL (modified line 6) Gottingen 451 airfoil Max thickness 4.4% at 30% chord. Max camber 5.6% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 451 AIRFOIL (modified line 6)
17. 17.
0.0000000 0.0000000
0.0124600 0.0120400
0.0249500 0.0192624
0.0499100 0.0291500
0.0748900 0.0372200
0.0998600 0.0453000
0.1498300 0.0569500
0.1998000 0.0651000
0.2997800 0.0744000
0.3997700 0.0772000
0.4997800 0.0740000
0.5998000 0.0658000
0.6998400 0.0531000
0.7998800 0.0384000
0.8999400 0.0212000
0.9499700 0.0113500
1.0000000 0.0000000
0.0000000 0.0000000
0.0125100 -.0019600
0.0250000 -.0004200
0.0499900 0.0031500
0.0749800 0.0067200
0.0999700 0.0098000
0.1499500 0.0174500
0.1999300 0.0226000
0.2999100 0.0304000
0.3999000 0.0342000
0.4999000 0.0335000
0.5999100 0.0298000
0.6999300 0.0241000
0.7999500 0.0174000
0.8999700 0.0087000
0.9499800 0.0058500
1.0000000 0.0000000
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Polars for GOE 451 AIRFOIL (modified line 6) (goe451-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe451-il | 50,000 | 9 | 36.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe451-il | 100,000 | 9 | 29.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe451-il | 200,000 | 9 | 50.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe451-il | 500,000 | 9 | 37.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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