GOE 437 AIRFOIL (goe437-il)
GOE 437 AIRFOIL - Gottingen 437 airfoil
| Details | Dat file | Parser | |
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(goe437-il) GOE 437 AIRFOIL Gottingen 437 airfoil Max thickness 7.1% at 30% chord. Max camber 4.8% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 437 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0145900
0.0250000 0.0227700
0.0500000 0.0363500
0.0750000 0.0465300
0.1000000 0.0547000
0.1500000 0.0670500
0.2000000 0.0754000
0.3000000 0.0821000
0.4000000 0.0813000
0.5000000 0.0750000
0.6000000 0.0662000
0.7000000 0.0529000
0.8000000 0.0381000
0.9000000 0.0208000
0.9500000 0.0106500
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0054100
0.0250000 -.0068300
0.0500000 -.0066500
0.0750000 -.0054800
0.1000000 -.0028000
0.1500000 0.0020500
0.2000000 0.0064000
0.3000000 0.0116000
0.4000000 0.0148000
0.5000000 0.0165000
0.6000000 0.0157000
0.7000000 0.0134000
0.8000000 0.0091000
0.9000000 0.0043000
0.9500000 0.0021500
1.0000000 0.0000000
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Similar airfoils
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Polars for GOE 437 AIRFOIL (goe437-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe437-il | 50,000 | 9 | 41.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe437-il | 50,000 | 5 | 42.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe437-il | 100,000 | 9 | 59.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe437-il | 100,000 | 5 | 60.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe437-il | 200,000 | 9 | 78.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe437-il | 200,000 | 5 | 80 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe437-il | 500,000 | 9 | 106.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe437-il | 500,000 | 5 | 105.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe437-il | 1,000,000 | 9 | 128.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe437-il | 1,000,000 | 5 | 123.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||