GOE 741 AIRFOIL (goe741-il)
GOE 741 AIRFOIL - Gottingen 741 airfoil
| Details | Dat file | Parser | |
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(goe741-il) GOE 741 AIRFOIL Gottingen 741 airfoil Max thickness 15.3% at 30% chord. Max camber 4.8% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 741 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0307300
0.0250000 0.0444600
0.0500000 0.0639200
0.0750000 0.0793900
0.1000000 0.0908500
0.1500000 0.1080700
0.2000000 0.1180000
0.3000000 0.1248500
0.4000000 0.1171000
0.5000000 0.0982500
0.6000000 0.0751000
0.7000000 0.0499500
0.8000000 0.0268000
0.9000000 0.0091500
0.9500000 0.0033800
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0212700
0.0250000 -.0267400
0.0500000 -.0317800
0.0750000 -.0341100
0.1000000 -.0346500
0.1500000 -.0347300
0.2000000 -.0323000
0.3000000 -.0284500
0.4000000 -.0271000
0.5000000 -.0277500
0.6000000 -.0264000
0.7000000 -.0245500
0.8000000 -.0224000
0.9000000 -.0138500
0.9500000 -.0074300
1.0000000 0.0000000
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Polars for GOE 741 AIRFOIL (goe741-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe741-il | 50,000 | 9 | 3.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe741-il | 50,000 | 5 | 14.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe741-il | 100,000 | 9 | 17.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe741-il | 100,000 | 5 | 39 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe741-il | 200,000 | 9 | 61.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe741-il | 200,000 | 5 | 66.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe741-il | 500,000 | 9 | 101.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe741-il | 500,000 | 5 | 93 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe741-il | 1,000,000 | 9 | 122.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe741-il | 1,000,000 | 5 | 106.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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