WORTMANN FX 63-137 AIRFOIL (fx63137-il)
WORTMANN FX 63-137 AIRFOIL - Wortmann FX 63-137 human power aircraft airfoil (Liver Puffin) airfoil
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(fx63137-il) WORTMANN FX 63-137 AIRFOIL Wortmann FX 63-137 human power aircraft airfoil (Liver Puffin) airfoil Max thickness 13.7% at 30.9% chord. Max camber 6% at 53.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
WORTMANN FX 63-137 AIRFOIL
49.0 49.0
0.000000 0.000000
0.001070 0.009000
0.004280 0.017500
0.009610 0.027400
0.017040 0.036250
0.026530 0.044800
0.038060 0.052480
0.051560 0.060050
0.066990 0.068360
0.084270 0.075550
0.103320 0.083130
0.124080 0.089610
0.146450 0.096220
0.170330 0.101650
0.195620 0.107040
0.222210 0.111220
0.250000 0.115220
0.278860 0.117920
0.308660 0.120240
0.339280 0.121280
0.370590 0.121910
0.402450 0.121370
0.434740 0.120420
0.467300 0.118330
0.500000 0.115780
0.532700 0.112210
0.565260 0.108230
0.597550 0.103310
0.629410 0.098040
0.660720 0.092040
0.691340 0.085900
0.721140 0.079270
0.750000 0.072730
0.777790 0.066050
0.804380 0.059620
0.829670 0.053230
0.853550 0.047110
0.875920 0.041140
0.896680 0.035530
0.915730 0.030180
0.933010 0.025160
0.948440 0.020430
0.961940 0.016010
0.973470 0.011890
0.982960 0.008180
0.990390 0.005010
0.995720 0.002490
0.998930 0.000820
1.000000 0.000000
0.000000 0.000000
0.001070 -0.002320
0.004280 -0.005660
0.009610 -0.009950
0.017040 -0.012540
0.026530 -0.015370
0.038060 -0.016980
0.051560 -0.018870
0.066990 -0.019920
0.084270 -0.021220
0.103320 -0.021800
0.124080 -0.022560
0.146450 -0.022630
0.170330 -0.022770
0.195620 -0.022200
0.222210 -0.021610
0.250000 -0.020340
0.278860 -0.018950
0.308660 -0.016880
0.339280 -0.014600
0.370590 -0.011670
0.402450 -0.008480
0.434740 -0.004860
0.467300 -0.001030
0.500000 0.003070
0.532700 0.007160
0.565260 0.011120
0.597550 0.014750
0.629410 0.018130
0.660720 0.020980
0.691340 0.023450
0.721140 0.025300
0.750000 0.026680
0.777790 0.027450
0.804380 0.027680
0.829670 0.027290
0.853550 0.026310
0.875920 0.024790
0.896680 0.022840
0.915730 0.020520
0.933010 0.017940
0.948440 0.015140
0.961940 0.012190
0.973470 0.009210
0.982960 0.006300
0.990390 0.003730
0.995720 0.001690
0.998930 0.000400
1.000000 0.000000
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Polars for WORTMANN FX 63-137 AIRFOIL (fx63137-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx63137-il | 50,000 | 9 | 26.8 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137-il | 50,000 | 5 | 31.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137-il | 100,000 | 9 | 62.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137-il | 100,000 | 5 | 63.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137-il | 200,000 | 9 | 90.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137-il | 200,000 | 5 | 85.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137-il | 500,000 | 9 | 119.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137-il | 500,000 | 5 | 103.6 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137-il | 1,000,000 | 9 | 132.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137-il | 1,000,000 | 5 | 105.7 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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