FX 63-110 AIRFOIL (fx63110-il)
FX 63-110 AIRFOIL - Wortmann FX 63-110 airfoil
| Details | Dat file | Parser | |
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(fx63110-il) FX 63-110 AIRFOIL Wortmann FX 63-110 airfoil Max thickness 11% at 30.8% chord. Max camber 4.3% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 63-110 AIRFOIL
18. 16.
0.0000000 0.0000000
0.0090000 0.0214700
0.0260000 0.0343700
0.0380000 0.0410400
0.0670000 0.0532500
0.1030000 0.0648400
0.1460000 0.0748700
0.1960000 0.0831800
0.2500000 0.0894300
0.3080000 0.0931500
0.4020000 0.0936300
0.5000000 0.0889300
0.5970000 0.0788800
0.6910000 0.0651600
0.8040000 0.0447600
0.8960000 0.0264100
0.9480000 0.0151100
1.0000000 0.0000000
0.0000000 0.0000000
0.0090000 -.0087700
0.0260000 -.0143700
0.1030000 -.0202400
0.1460000 -.0211700
0.1960000 -.0212800
0.2500000 -.0201300
0.3080000 -.0168500
0.4020000 -.0097300
0.5000000 -.0020800
0.5970000 0.0073200
0.6910000 0.0146400
0.8040000 0.0189400
0.8960000 0.0159900
0.9480000 0.0107900
1.0000000 0.0000000
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Polars for FX 63-110 AIRFOIL (fx63110-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx63110-il | 50,000 | 9 | 40 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63110-il | 50,000 | 5 | 42.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63110-il | 100,000 | 9 | 64.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63110-il | 100,000 | 5 | 66.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63110-il | 200,000 | 9 | 90.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63110-il | 200,000 | 5 | 87.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63110-il | 500,000 | 9 | 118.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63110-il | 500,000 | 5 | 105.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63110-il | 1,000,000 | 9 | 136.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63110-il | 1,000,000 | 5 | 117.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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