GOE 400 AIRFOIL (goe400-il)
GOE 400 AIRFOIL - Gottingen 400 airfoil
| Details | Dat file | Parser | |
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(goe400-il) GOE 400 AIRFOIL Gottingen 400 airfoil Max thickness 6.1% at 20% chord. Max camber 4.9% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 400 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0171700
0.0250000 0.0256400
0.0500000 0.0381800
0.0750000 0.0465100
0.1000000 0.0538500
0.1500000 0.0645200
0.2000000 0.0714000
0.3000000 0.0770500
0.4000000 0.0751000
0.5000000 0.0675500
0.6000000 0.0560000
0.7000000 0.0427500
0.8000000 0.0293000
0.9000000 0.0151500
0.9500000 0.0078300
1.0000000 0.0008000
0.0000000 0.0000000
0.0125000 -.0108300
0.0250000 -.0126600
0.0500000 -.0123200
0.0750000 -.0098900
0.1000000 -.0046500
0.1500000 0.0035200
0.2000000 0.0102000
0.3000000 0.0190500
0.4000000 0.0227000
0.5000000 0.0224500
0.6000000 0.0194000
0.7000000 0.0139500
0.8000000 0.0083000
0.9000000 0.0036500
0.9500000 0.0015300
1.0000000 0.0000000
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Polars for GOE 400 AIRFOIL (goe400-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe400-il | 50,000 | 9 | 37.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe400-il | 50,000 | 5 | 41.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe400-il | 100,000 | 9 | 59.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe400-il | 100,000 | 5 | 61.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe400-il | 200,000 | 9 | 81 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe400-il | 200,000 | 5 | 79.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe400-il | 500,000 | 9 | 109.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe400-il | 500,000 | 5 | 88.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe400-il | 1,000,000 | 9 | 126 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe400-il | 1,000,000 | 5 | 101.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||