GOE 599 AIRFOIL (goe599-il)
GOE 599 AIRFOIL - Gottingen 599 airfoil
| Details | Dat file | Parser | |
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(goe599-il) GOE 599 AIRFOIL Gottingen 599 airfoil Max thickness 10% at 29.6% chord. Max camber 1.5% at 59.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 599 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0116500 0.0146800
0.0237600 0.0213800
0.0483200 0.0288100
0.0729500 0.0352500
0.0976300 0.0406900
0.1471700 0.0485700
0.1967700 0.0554600
0.2963800 0.0622600
0.3963000 0.0635800
0.4964200 0.0614200
0.5967500 0.0557600
0.6972899 0.0466200
0.7979900 0.0344800
0.8987900 0.0208500
0.9493100 0.0118000
1.0000000 0.0017500
0.0000000 0.0000000
0.0132200 -.0122300
0.0259900 -.0169900
0.0513700 -.0235100
0.0766400 -.0280400
0.1017800 -.0305700
0.1520500 -.0351400
0.2021700 -.0372200
0.3021800 -.0374000
0.4020500 -.0350800
0.5017900 -.0307700
0.6014600 -.0249700
0.7011200 -.0191600
0.8007801 -.0133500
0.9004400 -.0075500
0.9502700 -.0046500
1.0000000 -.0017500
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Polars for GOE 599 AIRFOIL (goe599-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe599-il | 50,000 | 9 | 34.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe599-il | 50,000 | 5 | 33.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe599-il | 100,000 | 9 | 48.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe599-il | 100,000 | 5 | 44.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe599-il | 200,000 | 9 | 61.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe599-il | 200,000 | 5 | 51.2 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe599-il | 500,000 | 9 | 72.8 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe599-il | 500,000 | 5 | 65.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe599-il | 1,000,000 | 9 | 79.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe599-il | 1,000,000 | 5 | 80.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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