WORTMANN FX 76-120 (fx76120-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 76-120 (fx76120-il) Reynolds number: 50,000 Max Cl/Cd: 26.69 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx76120-il-50000-n5.txt Download as CSV file: xf-fx76120-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 76-120
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7463 0.09139 0.08329 -0.0265 1.0000 0.0817
-12.250 -0.8020 0.07751 0.06929 -0.0356 1.0000 0.0804
-12.000 -0.8451 0.06853 0.06012 -0.0406 1.0000 0.0797
-11.750 -0.8746 0.06273 0.05410 -0.0421 1.0000 0.0797
-11.500 -0.8976 0.05838 0.04951 -0.0416 1.0000 0.0805
-11.250 -0.9159 0.05484 0.04568 -0.0397 1.0000 0.0815
-11.000 -0.9318 0.05172 0.04223 -0.0367 1.0000 0.0830
-10.750 -0.9282 0.04950 0.03994 -0.0348 1.0000 0.0852
-10.500 -0.9213 0.04767 0.03805 -0.0331 1.0000 0.0878
-10.250 -0.9171 0.04562 0.03581 -0.0310 1.0000 0.0911
-10.000 -0.9144 0.04325 0.03306 -0.0287 1.0000 0.0951
-9.750 -0.9025 0.04164 0.03146 -0.0271 1.0000 0.0990
-9.500 -0.8914 0.04007 0.02977 -0.0253 1.0000 0.1036
-9.250 -0.8811 0.03822 0.02762 -0.0233 1.0000 0.1096
-9.000 -0.8674 0.03702 0.02650 -0.0216 1.0000 0.1153
-8.750 -0.8541 0.03544 0.02466 -0.0197 1.0000 0.1230
-8.500 -0.8403 0.03436 0.02367 -0.0179 1.0000 0.1306
-8.250 -0.8258 0.03311 0.02230 -0.0160 1.0000 0.1399
-8.000 -0.8113 0.03196 0.02100 -0.0141 1.0000 0.1515
-7.750 -0.7969 0.03102 0.02013 -0.0122 1.0000 0.1630
-7.500 -0.7821 0.03009 0.01920 -0.0102 1.0000 0.1761
-7.250 -0.7670 0.02923 0.01829 -0.0083 1.0000 0.1908
-7.000 -0.7517 0.02843 0.01748 -0.0063 1.0000 0.2066
-6.750 -0.7358 0.02769 0.01671 -0.0044 1.0000 0.2228
-6.500 -0.7194 0.02699 0.01599 -0.0025 1.0000 0.2397
-6.250 -0.7027 0.02633 0.01531 -0.0007 1.0000 0.2570
-6.000 -0.6855 0.02570 0.01465 0.0011 1.0000 0.2746
-5.750 -0.6679 0.02510 0.01402 0.0029 1.0000 0.2926
-5.500 -0.6498 0.02452 0.01345 0.0046 1.0000 0.3106
-5.250 -0.6313 0.02396 0.01293 0.0062 1.0000 0.3286
-5.000 -0.6125 0.02342 0.01243 0.0079 1.0000 0.3473
-4.750 -0.5934 0.02290 0.01195 0.0094 1.0000 0.3666
-4.500 -0.5740 0.02240 0.01149 0.0110 1.0000 0.3873
-4.250 -0.5546 0.02192 0.01102 0.0125 1.0000 0.4098
-4.000 -0.5352 0.02146 0.01067 0.0141 1.0000 0.4328
-3.750 -0.5160 0.02102 0.01031 0.0157 1.0000 0.4591
-3.500 -0.4969 0.02061 0.01005 0.0173 1.0000 0.4867
-3.250 -0.4786 0.02025 0.00981 0.0192 1.0000 0.5171
-3.000 -0.4607 0.01994 0.00965 0.0212 1.0000 0.5511
-2.750 -0.4425 0.01967 0.00954 0.0233 1.0000 0.5881
-2.500 -0.4239 0.01947 0.00950 0.0253 1.0000 0.6282
-2.250 -0.4037 0.01936 0.00957 0.0273 1.0000 0.6697
-2.000 -0.3824 0.01934 0.00969 0.0290 1.0000 0.7132
-1.750 -0.3578 0.01943 0.00990 0.0302 1.0000 0.7564
-1.500 -0.3300 0.01960 0.01014 0.0308 1.0000 0.7982
-1.250 -0.2972 0.01986 0.01043 0.0303 1.0000 0.8374
-1.000 -0.2606 0.02017 0.01072 0.0289 1.0000 0.8738
-0.750 -0.2167 0.02052 0.01105 0.0259 0.9997 0.9055
-0.500 -0.1479 0.02094 0.01140 0.0179 0.9891 0.9289
-0.250 -0.0733 0.02124 0.01165 0.0089 0.9778 0.9470
0.000 0.0001 0.02133 0.01173 0.0000 0.9634 0.9634
0.250 0.0732 0.02124 0.01166 -0.0089 0.9471 0.9780
0.500 0.1482 0.02093 0.01139 -0.0180 0.9289 0.9892
0.750 0.2169 0.02052 0.01104 -0.0259 0.9052 0.9997
1.000 0.2606 0.02017 0.01072 -0.0289 0.8737 1.0000
1.250 0.2971 0.01986 0.01043 -0.0303 0.8375 1.0000
1.500 0.3300 0.01960 0.01014 -0.0308 0.7982 1.0000
1.750 0.3578 0.01942 0.00990 -0.0302 0.7562 1.0000
2.000 0.3824 0.01934 0.00969 -0.0290 0.7132 1.0000
2.250 0.4037 0.01936 0.00956 -0.0272 0.6697 1.0000
2.500 0.4239 0.01947 0.00949 -0.0253 0.6285 1.0000
2.750 0.4425 0.01967 0.00954 -0.0233 0.5881 1.0000
3.000 0.4607 0.01994 0.00965 -0.0212 0.5512 1.0000
3.250 0.4786 0.02025 0.00981 -0.0192 0.5172 1.0000
3.500 0.4968 0.02061 0.01005 -0.0173 0.4866 1.0000
3.750 0.5160 0.02102 0.01030 -0.0157 0.4589 1.0000
4.000 0.5352 0.02145 0.01067 -0.0141 0.4329 1.0000
4.250 0.5546 0.02192 0.01102 -0.0125 0.4099 1.0000
4.500 0.5741 0.02240 0.01149 -0.0110 0.3875 1.0000
4.750 0.5934 0.02290 0.01195 -0.0094 0.3666 1.0000
5.000 0.6125 0.02342 0.01243 -0.0079 0.3472 1.0000
5.250 0.6313 0.02396 0.01293 -0.0062 0.3286 1.0000
5.500 0.6498 0.02452 0.01345 -0.0046 0.3107 1.0000
5.750 0.6679 0.02510 0.01402 -0.0029 0.2926 1.0000
6.000 0.6855 0.02570 0.01465 -0.0011 0.2746 1.0000
6.250 0.7028 0.02633 0.01531 0.0007 0.2571 1.0000
6.500 0.7195 0.02699 0.01599 0.0025 0.2398 1.0000
6.750 0.7357 0.02768 0.01671 0.0044 0.2227 1.0000
7.000 0.7516 0.02842 0.01747 0.0063 0.2064 1.0000
7.250 0.7670 0.02923 0.01831 0.0083 0.1908 1.0000
7.500 0.7821 0.03009 0.01920 0.0102 0.1762 1.0000
7.750 0.7970 0.03102 0.02012 0.0122 0.1630 1.0000
8.000 0.8115 0.03196 0.02102 0.0141 0.1516 1.0000
8.250 0.8260 0.03311 0.02231 0.0160 0.1400 1.0000
8.500 0.8403 0.03435 0.02366 0.0179 0.1305 1.0000
8.750 0.8541 0.03543 0.02465 0.0197 0.1229 1.0000
9.000 0.8674 0.03700 0.02649 0.0216 0.1152 1.0000
9.250 0.8810 0.03820 0.02759 0.0233 0.1094 1.0000
9.500 0.8915 0.04005 0.02977 0.0252 0.1036 1.0000
9.750 0.9028 0.04165 0.03147 0.0270 0.0990 1.0000
10.000 0.9149 0.04327 0.03308 0.0286 0.0952 1.0000
10.250 0.9175 0.04563 0.03583 0.0310 0.0912 1.0000
10.500 0.9215 0.04769 0.03807 0.0330 0.0878 1.0000
10.750 0.9286 0.04950 0.03993 0.0348 0.0851 1.0000
11.000 0.9315 0.05175 0.04226 0.0367 0.0829 1.0000
11.250 0.9163 0.05484 0.04568 0.0396 0.0815 1.0000
11.500 0.8977 0.05842 0.04954 0.0415 0.0804 1.0000
11.750 0.8753 0.06272 0.05408 0.0420 0.0797 1.0000
12.000 0.8451 0.06860 0.06019 0.0405 0.0796 1.0000
12.250 0.8020 0.07760 0.06938 0.0354 0.0803 1.0000
12.500 0.7457 0.09170 0.08360 0.0261 0.0816 1.0000
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