WORTMANN FX M2 AIRFOIL (fxm2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX M2 AIRFOIL (fxm2-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.42 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fxm2-il-1000000.txt Download as CSV file: xf-fxm2-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX M2 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1264 0.08726 0.08444 -0.0451 0.6491 0.0110
-8.750 -0.1219 0.08455 0.08153 -0.0455 0.5937 0.0112
-8.500 -0.1209 0.08074 0.07771 -0.0475 0.5861 0.0118
-8.250 -0.1171 0.07725 0.07429 -0.0491 0.6019 0.0118
-8.000 -0.1148 0.07442 0.07125 -0.0497 0.5406 0.0118
-7.750 -0.1103 0.07129 0.06812 -0.0506 0.5333 0.0118
-7.250 -0.1342 0.07581 0.07246 -0.0568 0.5268 0.0120
-7.000 -0.1310 0.07386 0.07041 -0.0566 0.4884 0.0121
-6.750 -0.1233 0.07175 0.06826 -0.0573 0.4791 0.0123
-6.500 -0.1135 0.06944 0.06593 -0.0590 0.4684 0.0125
-6.250 -0.1022 0.06688 0.06334 -0.0612 0.4569 0.0126
-5.750 -0.0748 0.06138 0.05769 -0.0669 0.4149 0.0133
-5.500 -0.0572 0.05830 0.05457 -0.0704 0.4091 0.0140
-5.250 -0.0278 0.05310 0.04927 -0.0789 0.4027 0.0149
-5.000 -0.0038 0.04926 0.04534 -0.0828 0.3973 0.0149
-4.750 0.0213 0.04528 0.04127 -0.0863 0.3872 0.0150
-4.500 0.0438 0.04046 0.03626 -0.0898 0.3638 0.0152
-4.250 0.0652 0.03875 0.03445 -0.0906 0.3510 0.0154
-4.000 0.0897 0.03689 0.03248 -0.0918 0.3442 0.0158
-3.750 0.1276 0.03292 0.02824 -0.0946 0.3392 0.0184
-3.500 0.1577 0.02953 0.02460 -0.0961 0.3308 0.0184
-3.250 0.1825 0.02662 0.02150 -0.0977 0.3035 0.0189
-3.000 0.2083 0.02561 0.02033 -0.0981 0.2923 0.0194
-2.750 0.2419 0.02392 0.01830 -0.0980 0.2864 0.0223
-2.500 0.2716 0.02031 0.01437 -0.0993 0.2818 0.0228
-2.250 0.2987 0.01951 0.01351 -0.0996 0.2771 0.0232
-2.000 0.3266 0.01871 0.01260 -0.0998 0.2685 0.0240
-0.750 0.4741 0.01302 0.00564 -0.0995 0.2279 0.0264
-0.500 0.5024 0.01237 0.00487 -0.0994 0.2249 0.0278
-0.250 0.5298 0.01230 0.00480 -0.0992 0.2216 0.0293
0.000 0.5585 0.01179 0.00423 -0.0990 0.2196 0.0297
0.250 0.5869 0.01145 0.00384 -0.0988 0.2164 0.0303
0.500 0.6150 0.01122 0.00357 -0.0986 0.2123 0.0310
0.750 0.6430 0.01131 0.00358 -0.0983 0.2088 0.0321
1.000 0.6718 0.01072 0.00304 -0.0984 0.2037 0.0335
1.250 0.6998 0.01065 0.00287 -0.0983 0.1850 0.0346
1.500 0.7277 0.01061 0.00277 -0.0981 0.1792 0.0356
1.750 0.7555 0.01061 0.00273 -0.0979 0.1737 0.0367
2.000 0.7833 0.01066 0.00275 -0.0977 0.1704 0.0380
2.250 0.8118 0.01054 0.00262 -0.0976 0.1683 0.0398
2.500 0.8397 0.01056 0.00263 -0.0975 0.1646 0.0415
2.750 0.8674 0.01063 0.00267 -0.0972 0.1607 0.0433
3.000 0.8948 0.01073 0.00274 -0.0970 0.1564 0.0452
3.250 0.9226 0.01078 0.00279 -0.0968 0.1541 0.0498
3.500 0.9503 0.01083 0.00287 -0.0966 0.1511 0.0640
3.750 0.9788 0.01073 0.00304 -0.0968 0.1449 0.2662
4.000 1.0086 0.01018 0.00334 -0.0977 0.1374 0.6991
4.500 1.0523 0.01019 0.00372 -0.0949 0.1083 1.0000
4.750 1.0785 0.01051 0.00395 -0.0945 0.0980 1.0000
5.000 1.1044 0.01086 0.00420 -0.0941 0.0866 1.0000
5.250 1.1309 0.01112 0.00442 -0.0938 0.0839 1.0000
5.500 1.1573 0.01137 0.00463 -0.0935 0.0813 1.0000
5.750 1.1837 0.01161 0.00484 -0.0931 0.0790 1.0000
6.000 1.2102 0.01184 0.00505 -0.0928 0.0774 1.0000
6.250 1.2367 0.01205 0.00527 -0.0925 0.0766 1.0000
6.500 1.2630 0.01227 0.00548 -0.0922 0.0761 1.0000
6.750 1.2893 0.01250 0.00571 -0.0919 0.0756 1.0000
7.000 1.3154 0.01273 0.00594 -0.0915 0.0750 1.0000
7.250 1.3414 0.01297 0.00619 -0.0912 0.0745 1.0000
7.500 1.3672 0.01322 0.00645 -0.0908 0.0740 1.0000
7.750 1.3929 0.01348 0.00671 -0.0905 0.0736 1.0000
8.000 1.4184 0.01374 0.00699 -0.0901 0.0732 1.0000
8.250 1.4438 0.01401 0.00729 -0.0897 0.0728 1.0000
8.500 1.4690 0.01429 0.00758 -0.0893 0.0724 1.0000
8.750 1.4939 0.01460 0.00790 -0.0888 0.0718 1.0000
9.000 1.5184 0.01494 0.00826 -0.0883 0.0707 1.0000
9.250 1.5428 0.01528 0.00862 -0.0878 0.0696 1.0000
9.500 1.5672 0.01561 0.00897 -0.0873 0.0690 1.0000
9.750 1.5913 0.01595 0.00934 -0.0868 0.0685 1.0000
10.000 1.6151 0.01631 0.00975 -0.0862 0.0678 1.0000
10.250 1.6387 0.01668 0.01016 -0.0856 0.0673 1.0000
10.500 1.6625 0.01699 0.01051 -0.0851 0.0672 1.0000
10.750 1.6862 0.01731 0.01087 -0.0845 0.0670 1.0000
11.000 1.7096 0.01763 0.01124 -0.0839 0.0668 1.0000
11.250 1.7328 0.01796 0.01163 -0.0833 0.0666 1.0000
11.500 1.7556 0.01830 0.01202 -0.0827 0.0662 1.0000
11.750 1.7782 0.01866 0.01244 -0.0820 0.0658 1.0000
12.000 1.8003 0.01903 0.01287 -0.0813 0.0652 1.0000
12.250 1.8221 0.01941 0.01331 -0.0805 0.0646 1.0000
12.500 1.8433 0.01982 0.01378 -0.0796 0.0638 1.0000
12.750 1.8639 0.02025 0.01427 -0.0787 0.0627 1.0000
13.000 1.8839 0.02071 0.01478 -0.0777 0.0613 1.0000
13.250 1.9023 0.02127 0.01536 -0.0766 0.0590 1.0000
13.500 1.9213 0.02174 0.01587 -0.0755 0.0554 1.0000
13.750 1.9365 0.02245 0.01654 -0.0739 0.0506 1.0000
14.000 1.9490 0.02319 0.01728 -0.0719 0.0491 1.0000
14.250 1.9584 0.02397 0.01810 -0.0694 0.0475 1.0000
14.500 1.9662 0.02483 0.01901 -0.0668 0.0462 1.0000
14.750 1.9717 0.02588 0.02014 -0.0640 0.0454 1.0000
15.000 1.9753 0.02710 0.02144 -0.0613 0.0447 1.0000
15.250 1.9767 0.02854 0.02297 -0.0587 0.0440 1.0000
15.500 1.9761 0.03022 0.02473 -0.0562 0.0432 1.0000
15.750 1.9750 0.03207 0.02668 -0.0540 0.0426 1.0000
16.000 1.9734 0.03411 0.02882 -0.0523 0.0421 1.0000
16.250 1.9702 0.03649 0.03131 -0.0510 0.0416 1.0000
16.500 1.9647 0.03935 0.03429 -0.0501 0.0412 1.0000
16.750 1.9562 0.04288 0.03795 -0.0500 0.0408 1.0000
17.000 1.9506 0.04641 0.04162 -0.0504 0.0406 1.0000
17.250 1.9420 0.05068 0.04604 -0.0515 0.0403 1.0000
17.500 1.9291 0.05589 0.05141 -0.0533 0.0400 1.0000
17.750 1.9106 0.06229 0.05798 -0.0560 0.0398 1.0000
18.000 1.8855 0.07009 0.06596 -0.0596 0.0397 1.0000
18.250 1.8529 0.07948 0.07554 -0.0641 0.0397 1.0000
18.500 1.8141 0.09024 0.08649 -0.0694 0.0398 1.0000
18.750 1.7733 0.10168 0.09812 -0.0754 0.0400 1.0000
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