GOE 425 AIRFOIL (goe425-il)
GOE 425 AIRFOIL - Gottingen 425 airfoil
| Details | Dat file | Parser | |
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(goe425-il) GOE 425 AIRFOIL Gottingen 425 airfoil Max thickness 16% at 29.3% chord. Max camber 4.5% at 39.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 425 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0111700 0.0249000
0.0230000 0.0374300
0.0470300 0.0554200
0.0713300 0.0686200
0.0957300 0.0797300
0.1448300 0.0966600
0.1941100 0.1099900
0.2933700 0.1238100
0.3933700 0.1237600
0.4940100 0.1118500
0.5950000 0.0934600
0.6962100 0.0707800
0.7974200 0.0481000
0.8986700 0.0248200
0.9493100 0.0129400
1.0000000 0.0005500
0.0000000 0.0000000
0.0134800 -.0182800
0.0262000 -.0224000
0.0514500 -.0270400
0.0766700 -.0310900
0.1017400 -.0324500
0.1518800 -.0351700
0.2019700 -.0367800
0.3019500 -.0363300
0.4017500 -.0325900
0.5013600 -.0254500
0.6009700 -.0181200
0.7006000 -.0121800
0.8004300 -.0080400
0.9002600 -.0047900
0.9501700 -.0032200
1.0000000 -.0005500
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Polars for GOE 425 AIRFOIL (goe425-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe425-il | 50,000 | 9 | 5.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe425-il | 50,000 | 5 | 17.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe425-il | 100,000 | 9 | 22.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe425-il | 100,000 | 5 | 44.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe425-il | 200,000 | 9 | 69.8 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe425-il | 200,000 | 5 | 74 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe425-il | 500,000 | 9 | 111 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe425-il | 500,000 | 5 | 108.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe425-il | 1,000,000 | 9 | 142.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe425-il | 1,000,000 | 5 | 132.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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