GOE 386 AIRFOIL (goe386-il)
GOE 386 AIRFOIL - Gottingen 386 airfoil
| Details | Dat file | Parser | |
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(goe386-il) GOE 386 AIRFOIL Gottingen 386 airfoil Max thickness 20.3% at 29% chord. Max camber 5.4% at 39% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 386 AIRFOIL
17. 17.
0.0000100 0.0000000
0.0100700 0.0358800
0.0214000 0.0531500
0.0447900 0.0769400
0.0685500 0.0952500
0.0926200 0.1088800
0.1412200 0.1295700
0.1903200 0.1428000
0.2896300 0.1530400
0.3897100 0.1518200
0.4906200 0.1383600
0.5920000 0.1180400
0.6935600 0.0950200
0.7954300 0.0674300
0.8976000 0.0354600
0.9487200 0.0189200
1.0000000 0.0016000
0.0000100 0.0000000
0.0144700 -.0289200
0.0276000 -.0382300
0.0531600 -.0466000
0.0784100 -.0501800
0.1036600 -.0538700
0.1537900 -.0557700
0.2036900 -.0542900
0.3033100 -.0488400
0.4028600 -.0420900
0.5024000 -.0353400
0.6019400 -.0285900
0.7014800 -.0218400
0.8010200 -.0150900
0.9005700 -.0083400
0.9503400 -.0049700
1.0000000 -.0016000
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Polars for GOE 386 AIRFOIL (goe386-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe386-il | 50,000 | 9 | 3.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe386-il | 50,000 | 5 | 16.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe386-il | 100,000 | 9 | 33.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe386-il | 100,000 | 5 | 40.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe386-il | 200,000 | 9 | 61.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe386-il | 200,000 | 5 | 59.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe386-il | 500,000 | 9 | 88.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe386-il | 500,000 | 5 | 76.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe386-il | 1,000,000 | 9 | 103.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe386-il | 1,000,000 | 5 | 94 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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