FX 63-137 13.7% smoothed (fx63137sm-il)
FX 63-137 13.7% smoothed - Wortmann FX 63-137 airfoil (smoothed)
| Details | Dat file | Parser | |
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(fx63137sm-il) FX 63-137 13.7% smoothed Wortmann FX 63-137 airfoil (smoothed) Max thickness 13.7% at 30.9% chord. Max camber 5.8% at 56.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
FX 63-137 13.7% smoothed 1.000000 0.000000 0.995720 0.002261 0.982960 0.008222 0.961940 0.016421 0.933010 0.025814 0.896680 0.036153 0.853550 0.047568 0.804380 0.060006 0.750000 0.073047 0.691340 0.085959 0.629410 0.097879 0.565260 0.107990 0.500000 0.115624 0.434740 0.120314 0.370590 0.121797 0.339280 0.121303 0.308660 0.119983 0.278860 0.117849 0.250000 0.114919 0.222210 0.111224 0.195620 0.106801 0.170330 0.101685 0.146450 0.095912 0.124080 0.089547 0.103320 0.082700 0.084270 0.075518 0.066990 0.068116 0.051560 0.060520 0.038060 0.052636 0.026530 0.044302 0.017040 0.035484 0.009610 0.026362 0.004280 0.017421 0.001070 0.009265 0.000000 0.002411 0.001070 -.002958 0.004280 -.007021 0.009610 -.010156 0.017040 -.012751 0.026530 -.015034 0.038060 -.017064 0.051560 -.018791 0.066990 -.020178 0.084270 -.021230 0.103320 -.021987 0.124080 -.022482 0.146450 -.022718 0.170330 -.022668 0.195620 -.022297 0.222210 -.021567 0.250000 -.020431 0.278860 -.018838 0.308660 -.016752 0.339280 -.014179 0.370590 -.011176 0.434740 -.004210 0.500000 0.003409 0.565260 0.010919 0.629410 0.017605 0.691340 0.022871 0.750000 0.026291 0.804380 0.027582 0.853550 0.026608 0.896680 0.023429 0.933010 0.018408 0.961940 0.012286 0.982960 0.006230 0.995720 0.001696 1.000000 0.000000 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
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Polars for FX 63-137 13.7% smoothed (fx63137sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx63137sm-il | 50,000 | 9 | 25.9 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137sm-il | 50,000 | 5 | 31.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137sm-il | 100,000 | 9 | 60.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137sm-il | 100,000 | 5 | 64.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137sm-il | 200,000 | 9 | 91.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137sm-il | 200,000 | 5 | 88.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137sm-il | 500,000 | 9 | 125.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137sm-il | 500,000 | 5 | 117.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137sm-il | 1,000,000 | 9 | 151.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137sm-il | 1,000,000 | 5 | 137.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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