WORTMANN FX 76-100 (fx76100-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 76-100 (fx76100-il) Reynolds number: 50,000 Max Cl/Cd: 26.13 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx76100-il-50000-n5.txt Download as CSV file: xf-fx76100-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 76-100
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7250 0.09544 0.08780 -0.0172 1.0000 0.0609
-11.500 -0.7482 0.08626 0.07862 -0.0232 1.0000 0.0606
-11.250 -0.7725 0.07833 0.07064 -0.0286 1.0000 0.0601
-11.000 -0.7983 0.07169 0.06390 -0.0323 1.0000 0.0596
-10.750 -0.8259 0.06627 0.05831 -0.0337 1.0000 0.0596
-10.500 -0.8482 0.06214 0.05399 -0.0327 1.0000 0.0596
-10.250 -0.8674 0.05819 0.04973 -0.0308 1.0000 0.0601
-10.000 -0.8805 0.05435 0.04546 -0.0287 1.0000 0.0610
-9.750 -0.8739 0.05181 0.04291 -0.0274 1.0000 0.0629
-9.500 -0.8681 0.04928 0.04022 -0.0258 1.0000 0.0649
-9.250 -0.8627 0.04641 0.03704 -0.0240 1.0000 0.0669
-9.000 -0.8550 0.04371 0.03397 -0.0222 1.0000 0.0696
-8.750 -0.8466 0.04102 0.03067 -0.0202 1.0000 0.0731
-8.500 -0.8306 0.03917 0.02890 -0.0190 1.0000 0.0769
-8.250 -0.8146 0.03718 0.02670 -0.0176 1.0000 0.0808
-8.000 -0.7981 0.03519 0.02432 -0.0160 1.0000 0.0864
-7.750 -0.7810 0.03375 0.02295 -0.0147 1.0000 0.0925
-7.500 -0.7616 0.03206 0.02095 -0.0133 1.0000 0.0996
-7.250 -0.7441 0.03077 0.01970 -0.0119 1.0000 0.1079
-7.000 -0.7258 0.02947 0.01835 -0.0105 1.0000 0.1184
-6.750 -0.7071 0.02823 0.01707 -0.0090 1.0000 0.1311
-6.500 -0.6891 0.02714 0.01600 -0.0075 1.0000 0.1477
-6.250 -0.6706 0.02611 0.01492 -0.0060 1.0000 0.1691
-6.000 -0.6528 0.02517 0.01408 -0.0044 1.0000 0.1925
-5.750 -0.6346 0.02433 0.01328 -0.0028 1.0000 0.2200
-5.500 -0.6161 0.02358 0.01256 -0.0013 1.0000 0.2485
-5.250 -0.5974 0.02290 0.01192 0.0003 1.0000 0.2783
-5.000 -0.5785 0.02226 0.01131 0.0018 1.0000 0.3090
-4.750 -0.5592 0.02164 0.01077 0.0033 1.0000 0.3401
-4.500 -0.5396 0.02104 0.01027 0.0049 1.0000 0.3721
-4.250 -0.5197 0.02047 0.00980 0.0064 1.0000 0.4055
-4.000 -0.4996 0.01991 0.00933 0.0079 1.0000 0.4412
-3.750 -0.4803 0.01939 0.00895 0.0097 1.0000 0.4794
-3.500 -0.4612 0.01891 0.00865 0.0117 1.0000 0.5206
-3.250 -0.4419 0.01848 0.00840 0.0137 1.0000 0.5667
-3.000 -0.4220 0.01813 0.00821 0.0158 1.0000 0.6170
-2.750 -0.4002 0.01787 0.00814 0.0177 1.0000 0.6693
-2.500 -0.3755 0.01773 0.00814 0.0193 1.0000 0.7232
-2.250 -0.3466 0.01772 0.00819 0.0201 1.0000 0.7757
-2.000 -0.3120 0.01782 0.00828 0.0197 1.0000 0.8234
-1.750 -0.2730 0.01797 0.00837 0.0183 1.0000 0.8666
-1.500 -0.2265 0.01814 0.00843 0.0152 1.0000 0.9023
-1.250 -0.1741 0.01828 0.00845 0.0108 1.0000 0.9324
-1.000 -0.1186 0.01834 0.00839 0.0053 1.0000 0.9587
-0.750 -0.0598 0.01827 0.00824 -0.0011 1.0000 0.9820
-0.500 -0.0088 0.01813 0.00805 -0.0064 1.0000 1.0000
-0.250 -0.0042 0.01803 0.00795 -0.0033 1.0000 1.0000
0.000 0.0000 0.01800 0.00791 0.0000 1.0000 1.0000
0.250 0.0043 0.01803 0.00795 0.0033 1.0000 1.0000
0.500 0.0089 0.01813 0.00804 0.0065 1.0000 1.0000
0.750 0.0602 0.01827 0.00824 0.0010 0.9818 1.0000
1.000 0.1183 0.01834 0.00839 -0.0053 0.9588 1.0000
1.250 0.1741 0.01828 0.00844 -0.0107 0.9324 1.0000
1.500 0.2267 0.01814 0.00843 -0.0153 0.9021 1.0000
1.750 0.2730 0.01797 0.00837 -0.0183 0.8665 1.0000
2.000 0.3120 0.01781 0.00828 -0.0197 0.8234 1.0000
2.250 0.3467 0.01772 0.00818 -0.0201 0.7754 1.0000
2.500 0.3754 0.01773 0.00814 -0.0192 0.7231 1.0000
2.750 0.4002 0.01787 0.00813 -0.0177 0.6691 1.0000
3.000 0.4219 0.01813 0.00821 -0.0158 0.6164 1.0000
3.250 0.4419 0.01848 0.00840 -0.0137 0.5665 1.0000
3.500 0.4612 0.01891 0.00865 -0.0117 0.5205 1.0000
3.750 0.4802 0.01939 0.00895 -0.0097 0.4791 1.0000
4.000 0.4996 0.01991 0.00933 -0.0079 0.4410 1.0000
4.250 0.5197 0.02046 0.00980 -0.0064 0.4056 1.0000
4.500 0.5396 0.02105 0.01027 -0.0049 0.3720 1.0000
4.750 0.5592 0.02164 0.01078 -0.0033 0.3402 1.0000
5.000 0.5785 0.02226 0.01131 -0.0018 0.3089 1.0000
5.250 0.5974 0.02290 0.01192 -0.0003 0.2784 1.0000
5.500 0.6161 0.02358 0.01256 0.0013 0.2487 1.0000
5.750 0.6346 0.02433 0.01328 0.0029 0.2199 1.0000
6.000 0.6528 0.02516 0.01407 0.0044 0.1923 1.0000
6.250 0.6706 0.02610 0.01494 0.0060 0.1685 1.0000
6.500 0.6891 0.02714 0.01600 0.0075 0.1475 1.0000
6.750 0.7070 0.02823 0.01706 0.0090 0.1309 1.0000
7.000 0.7257 0.02946 0.01834 0.0105 0.1182 1.0000
7.250 0.7441 0.03077 0.01970 0.0119 0.1076 1.0000
7.500 0.7616 0.03207 0.02095 0.0133 0.0995 1.0000
7.750 0.7810 0.03376 0.02295 0.0147 0.0924 1.0000
8.000 0.7981 0.03519 0.02432 0.0160 0.0864 1.0000
8.250 0.8147 0.03719 0.02671 0.0176 0.0808 1.0000
8.500 0.8307 0.03919 0.02892 0.0190 0.0769 1.0000
8.750 0.8467 0.04103 0.03068 0.0202 0.0732 1.0000
9.000 0.8552 0.04370 0.03396 0.0222 0.0696 1.0000
9.250 0.8627 0.04642 0.03704 0.0240 0.0668 1.0000
9.500 0.8683 0.04928 0.04021 0.0257 0.0649 1.0000
9.750 0.8735 0.05190 0.04302 0.0273 0.0631 1.0000
10.000 0.8811 0.05435 0.04544 0.0286 0.0610 1.0000
10.250 0.8675 0.05824 0.04978 0.0307 0.0601 1.0000
10.500 0.8486 0.06216 0.05402 0.0326 0.0596 1.0000
10.750 0.8261 0.06637 0.05842 0.0337 0.0596 1.0000
11.000 0.8014 0.07150 0.06369 0.0325 0.0598 1.0000
11.250 0.7777 0.07774 0.07004 0.0291 0.0603 1.0000
11.500 0.7491 0.08627 0.07862 0.0231 0.0606 1.0000
11.750 0.7270 0.09520 0.08756 0.0174 0.0610 1.0000
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Polar data table (+)
Polar graphs
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