GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il)
GOE 417A (GEW. PLATTE) AIRFOIL - Gottingen 417A (GEW. PLATTE) airfoil
| Details | Dat file | Parser | |
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(goe417a-il) GOE 417A (GEW. PLATTE) AIRFOIL Gottingen 417A (GEW. PLATTE) airfoil Max thickness 3.2% at 2.5% chord. Max camber 5.9% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 417A (GEW. PLATTE) AIRFOIL
16. 16.
0.0000000 0.0000000
0.0125000 0.0155000
0.0250000 0.0220000
0.0500000 0.0325000
0.0750000 0.0415000
0.1000000 0.0485000
0.1500000 0.0570000
0.2000000 0.0630000
0.3000000 0.0715000
0.4000000 0.0735000
0.5000000 0.0700000
0.6000000 0.0640000
0.7000000 0.0545000
0.8000000 0.0425000
0.9000000 0.0240000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0140000
0.0250000 -.0100000
0.0500000 0.0010000
0.0750000 0.0105000
0.1000000 0.0185000
0.1500000 0.0275000
0.2000000 0.0340000
0.3000000 0.0425000
0.4000000 0.0445000
0.5000000 0.0410000
0.6000000 0.0350000
0.7000000 0.0255000
0.8000000 0.0135000
0.9000000 -.0015000
1.0000000 0.0000000
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Polars for GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe417a-il | 50,000 | 9 | 46.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417a-il | 50,000 | 5 | 45.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417a-il | 100,000 | 9 | 65.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417a-il | 100,000 | 5 | 56.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417a-il | 200,000 | 9 | 71.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417a-il | 200,000 | 5 | 61.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417a-il | 500,000 | 9 | 75.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417a-il | 500,000 | 5 | 68.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417a-il | 1,000,000 | 9 | 86.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417a-il | 1,000,000 | 5 | 116.9 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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