WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il)
WORTMANN FX 66-17A-175 AIRFOIL - Wortmann FX 66-17A-175 airfoil
| Details | Dat file | Parser | |
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(fx66a175-il) WORTMANN FX 66-17A-175 AIRFOIL Wortmann FX 66-17A-175 airfoil Max thickness 17.5% at 33.9% chord. Max camber 4.2% at 40.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
WORTMANN FX 66-17A-175 AIRFOIL
44. 44.
0.000000 0.000000
0.001070 0.004710
0.004280 0.010260
0.009610 0.017130
0.017040 0.024960
0.026530 0.033470
0.038060 0.042400
0.051560 0.051610
0.066990 0.060870
0.084270 0.070110
0.103320 0.079110
0.124080 0.087830
0.146450 0.096040
0.170330 0.103750
0.195620 0.110670
0.222210 0.116850
0.250000 0.121920
0.278860 0.125860
0.308660 0.128090
0.339280 0.128890
0.370590 0.127680
0.402450 0.125150
0.434740 0.121020
0.467300 0.115930
0.500000 0.109860
0.532700 0.103380
0.565260 0.096470
0.597550 0.089520
0.629410 0.082500
0.660720 0.075690
0.691340 0.069060
0.721140 0.062740
0.750000 0.056560
0.777790 0.050690
0.804380 0.045060
0.829670 0.039750
0.853550 0.034690
0.875920 0.029990
0.915730 0.021460
0.948440 0.014160
0.973470 0.007810
0.990390 0.002410
0.998930 0.000140
1.000000 0.000000
0.000000 0.000000
0.001070 -0.002600
0.004280 -0.005930
0.009610 -0.009380
0.017040 -0.013070
0.026530 -0.016730
0.038060 -0.020430
0.051560 -0.023980
0.066990 -0.027460
0.084270 -0.030710
0.103320 -0.033810
0.124080 -0.036630
0.146450 -0.039210
0.170330 -0.041470
0.195620 -0.043400
0.222210 -0.044970
0.250000 -0.046060
0.278860 -0.046770
0.308660 -0.046830
0.339280 -0.046270
0.370590 -0.044580
0.402450 -0.042020
0.434740 -0.038070
0.467300 -0.033420
0.500000 -0.028530
0.532700 -0.023840
0.565260 -0.019390
0.597550 -0.015340
0.629410 -0.011730
0.660720 -0.008560
0.691340 -0.005900
0.721140 -0.003680
0.750000 -0.001910
0.777790 -0.000510
0.804380 0.000480
0.829670 0.001220
0.853550 0.001670
0.875920 0.001900
0.915730 0.001770
0.948440 0.001270
0.973470 0.000810
0.990390 0.000270
0.998930 0.000100
1.000000 0.000000
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Polars for WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx66a175-il | 50,000 | 9 | 4.9 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66a175-il | 50,000 | 5 | 12.3 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66a175-il | 100,000 | 9 | 12.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66a175-il | 100,000 | 5 | 34.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66a175-il | 200,000 | 9 | 70.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66a175-il | 200,000 | 5 | 71.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66a175-il | 500,000 | 9 | 103.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66a175-il | 500,000 | 5 | 100.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66a175-il | 1,000,000 | 9 | 128.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66a175-il | 1,000,000 | 5 | 124.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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