FX 71-L-150/30 AIRFOIL (fx711530-il)
FX 71-L-150/30 AIRFOIL - Wortmann FX 71-L-150/30 airfoil
| Details | Dat file | Parser | |
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(fx711530-il) FX 71-L-150/30 AIRFOIL Wortmann FX 71-L-150/30 airfoil Max thickness 15% at 33.9% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 71-L-150/30 AIRFOIL
44. 44.
0.000000 0.000000
0.001070 0.008130
0.004280 0.014370
0.009610 0.018960
0.017040 0.024420
0.026530 0.029450
0.038060 0.034650
0.051560 0.039580
0.066990 0.044500
0.084270 0.049020
0.103320 0.053540
0.124080 0.057530
0.146450 0.061360
0.170330 0.064670
0.195620 0.067740
0.222210 0.070140
0.250000 0.072290
0.278860 0.073690
0.308660 0.074770
0.339280 0.075000
0.370590 0.074860
0.402450 0.073720
0.434740 0.072190
0.467300 0.069690
0.500000 0.066670
0.532700 0.062710
0.565260 0.058450
0.597550 0.053630
0.629410 0.048500
0.660720 0.042640
0.691340 0.037290
0.721140 0.031400
0.750000 0.027420
0.777790 0.023470
0.804380 0.020400
0.829670 0.017090
0.853550 0.014480
0.875920 0.011770
0.915730 0.007560
0.948440 0.004350
0.973470 0.002270
0.990390 0.000890
0.998930 0.000100
1.000000 0.000000
0.000000 0.000000
0.001070 -0.008130
0.004280 -0.014370
0.009610 -0.018960
0.017040 -0.024420
0.026530 -0.029450
0.038060 -0.034650
0.051560 -0.039580
0.066990 -0.044500
0.084270 -0.049020
0.103320 -0.053540
0.124080 -0.057530
0.146450 -0.061360
0.170330 -0.064670
0.195620 -0.067740
0.222210 -0.070140
0.250000 -0.072290
0.278860 -0.073690
0.308660 -0.074770
0.339280 -0.075000
0.370590 -0.074860
0.402450 -0.073720
0.434740 -0.072190
0.467300 -0.069690
0.500000 -0.066670
0.532700 -0.062710
0.565260 -0.058450
0.597550 -0.053630
0.629410 -0.048500
0.660720 -0.042640
0.691340 -0.037290
0.721140 -0.031400
0.750000 -0.027420
0.777790 -0.023470
0.804380 -0.020400
0.829670 -0.017090
0.853550 -0.014480
0.875920 -0.011770
0.915730 -0.007560
0.948440 -0.004350
0.973470 -0.002270
0.990390 -0.000890
0.998930 -0.000100
1.000000 0.000000
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Polars for FX 71-L-150/30 AIRFOIL (fx711530-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx711530-il | 50,000 | 9 | 27.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711530-il | 50,000 | 5 | 26.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711530-il | 100,000 | 9 | 39.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711530-il | 100,000 | 5 | 35.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711530-il | 200,000 | 9 | 47.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711530-il | 200,000 | 5 | 40.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711530-il | 500,000 | 9 | 51.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711530-il | 500,000 | 5 | 49.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711530-il | 1,000,000 | 9 | 59.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711530-il | 1,000,000 | 5 | 58.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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