FX 63-100 AIRFOIL (fx63100-il)
FX 63-100 AIRFOIL - Wortmann FX 63-100 airfoil
| Details | Dat file | Parser | |
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(fx63100-il) FX 63-100 AIRFOIL Wortmann FX 63-100 airfoil Max thickness 9.9% 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 63-100 AIRFOIL
18. 16.
0.0000000 0.0000000
0.0090000 0.0200000
0.0260000 0.0320000
0.0380000 0.0383000
0.0670000 0.0498000
0.1030000 0.0607000
0.1460000 0.0702000
0.1960000 0.0781000
0.2500000 0.0841000
0.3080000 0.0878000
0.4020000 0.0886000
0.5000000 0.0845000
0.5970000 0.0754000
0.6910000 0.0627000
0.8040000 0.0435000
0.8960000 0.0259000
0.9480000 0.0149000
1.0000000 0.0000000
0.0000000 0.0000000
0.0090000 -.0073000
0.0260000 -.0120000
0.1030000 -.0161000
0.1460000 -.0165000
0.1960000 -.0162000
0.2500000 -.0148000
0.3080000 -.0115000
0.4020000 -.0047000
0.5000000 0.0023500
0.5970000 0.0108000
0.6910000 0.0171000
0.8040000 0.0202000
0.8960000 0.0165000
0.9480000 0.0110000
1.0000000 0.0000000
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Similar airfoils
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Polars for FX 63-100 AIRFOIL (fx63100-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx63100-il | 50,000 | 9 | 43 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63100-il | 50,000 | 5 | 44.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63100-il | 100,000 | 9 | 67 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63100-il | 100,000 | 5 | 67.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63100-il | 200,000 | 9 | 92.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63100-il | 200,000 | 5 | 90 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63100-il | 500,000 | 9 | 121.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63100-il | 500,000 | 5 | 106.2 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63100-il | 1,000,000 | 9 | 136.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63100-il | 1,000,000 | 5 | 115.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||