GOE 692 AIRFOIL (goe692-il)
GOE 692 AIRFOIL - Gottingen 692 airfoil
| Details | Dat file | Parser | |
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(goe692-il) GOE 692 AIRFOIL Gottingen 692 airfoil Max thickness 16.1% at 30% chord. Max camber 5% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 692 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0280900
0.0250000 0.0416900
0.0500000 0.0613700
0.0750000 0.0760600
0.1000000 0.0867500
0.1500000 0.1031300
0.2000000 0.1145000
0.3000000 0.1277500
0.4000000 0.1305000
0.5000000 0.1247500
0.6000000 0.1110000
0.7000000 0.0917500
0.8000000 0.0665000
0.9000000 0.0382500
0.9500000 0.0226300
1.0000000 0.0050000
0.0000000 0.0000000
0.0125000 -.0204100
0.0250000 -.0273100
0.0500000 -.0346300
0.0750000 -.0379400
0.1000000 -.0397500
0.1500000 -.0398700
0.2000000 -.0380000
0.3000000 -.0332500
0.4000000 -.0285000
0.5000000 -.0237500
0.6000000 -.0190000
0.7000000 -.0142500
0.8000000 -.0095000
0.9000000 -.0047500
0.9500000 -.0023700
1.0000000 0.0000000
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Polars for GOE 692 AIRFOIL (goe692-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe692-il | 50,000 | 9 | 7.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe692-il | 50,000 | 5 | 19 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe692-il | 100,000 | 9 | 48.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe692-il | 100,000 | 5 | 49.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe692-il | 200,000 | 9 | 76.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe692-il | 200,000 | 5 | 73.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe692-il | 500,000 | 9 | 109 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe692-il | 500,000 | 5 | 99.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe692-il | 1,000,000 | 9 | 132.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe692-il | 1,000,000 | 5 | 114.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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