WORTMANN FX M2 AIRFOIL (fxm2-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX M2 AIRFOIL (fxm2-il) Reynolds number: 500,000 Max Cl/Cd: 86.22 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fxm2-il-500000-n5.txt Download as CSV file: xf-fxm2-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3150 0.11805 0.11568 -0.0111 1.0000 0.0108
-9.750 -0.3098 0.11521 0.11286 -0.0116 1.0000 0.0113
-9.500 -0.3049 0.11235 0.11002 -0.0122 1.0000 0.0115
-9.250 -0.2927 0.10850 0.10618 -0.0153 0.9985 0.0116
-9.000 -0.2818 0.10480 0.10248 -0.0180 0.9936 0.0117
-8.750 -0.2725 0.10166 0.09936 -0.0197 0.9885 0.0117
-8.500 -0.2622 0.09798 0.09569 -0.0224 0.9793 0.0117
-8.000 -0.1507 0.08415 0.08068 -0.0534 0.6833 0.0117
-7.750 -0.1453 0.08259 0.07888 -0.0524 0.6186 0.0106
-7.500 -0.1406 0.08016 0.07634 -0.0529 0.5914 0.0110
-7.250 -0.1376 0.07744 0.07358 -0.0538 0.5648 0.0122
-7.000 -0.1348 0.07515 0.07121 -0.0540 0.5444 0.0122
-6.750 -0.1265 0.07382 0.06985 -0.0540 0.5302 0.0131
-6.500 -0.1179 0.07078 0.06679 -0.0579 0.5168 0.0148
-6.250 -0.1116 0.06627 0.06222 -0.0609 0.4945 0.0117
-6.000 -0.0990 0.06360 0.05947 -0.0631 0.4796 0.0115
-5.750 -0.0843 0.06050 0.05629 -0.0663 0.4638 0.0113
-5.500 -0.0667 0.05714 0.05288 -0.0700 0.4466 0.0111
-5.250 -0.0477 0.05353 0.04907 -0.0740 0.4155 0.0111
-5.000 -0.0247 0.04942 0.04485 -0.0785 0.4057 0.0112
-4.750 0.0066 0.04188 0.03707 -0.0863 0.4003 0.0119
-4.500 0.0314 0.03966 0.03472 -0.0882 0.3765 0.0121
-4.250 0.0561 0.03788 0.03274 -0.0895 0.3531 0.0125
-4.000 0.0838 0.03528 0.02996 -0.0914 0.3466 0.0129
-3.750 0.1134 0.03237 0.02684 -0.0933 0.3409 0.0139
-3.500 0.1492 0.02655 0.02054 -0.0962 0.3362 0.0152
-3.250 0.1765 0.02538 0.01923 -0.0966 0.3270 0.0155
-3.000 0.2044 0.02401 0.01764 -0.0971 0.3012 0.0161
-2.500 0.2675 0.01821 0.01089 -0.0983 0.2879 0.0187
-2.250 0.2953 0.01760 0.01012 -0.0983 0.2818 0.0190
-2.000 0.3234 0.01696 0.00934 -0.0983 0.2760 0.0196
-1.750 0.3523 0.01603 0.00821 -0.0983 0.2688 0.0204
-1.500 0.3817 0.01490 0.00682 -0.0982 0.2549 0.0215
-1.250 0.4097 0.01426 0.00591 -0.0980 0.2416 0.0228
-1.000 0.4373 0.01401 0.00555 -0.0978 0.2368 0.0234
-0.750 0.4651 0.01371 0.00515 -0.0976 0.2324 0.0241
-0.500 0.4929 0.01339 0.00473 -0.0973 0.2283 0.0250
-0.250 0.5206 0.01313 0.00435 -0.0970 0.2242 0.0259
0.000 0.5483 0.01296 0.00409 -0.0968 0.2205 0.0271
0.250 0.5762 0.01274 0.00390 -0.0966 0.2164 0.0281
0.500 0.6040 0.01260 0.00374 -0.0964 0.2119 0.0290
0.750 0.6320 0.01247 0.00358 -0.0962 0.2086 0.0300
1.000 0.6602 0.01234 0.00344 -0.0961 0.2038 0.0310
1.250 0.6880 0.01232 0.00338 -0.0958 0.1938 0.0322
1.500 0.7159 0.01224 0.00325 -0.0958 0.1847 0.0338
1.750 0.7436 0.01225 0.00321 -0.0956 0.1791 0.0350
2.000 0.7711 0.01231 0.00320 -0.0953 0.1729 0.0363
2.250 0.7987 0.01236 0.00323 -0.0951 0.1691 0.0376
2.500 0.8263 0.01240 0.00325 -0.0949 0.1650 0.0399
2.750 0.8538 0.01248 0.00331 -0.0947 0.1611 0.0423
3.000 0.8809 0.01260 0.00340 -0.0944 0.1576 0.0444
3.250 0.9082 0.01272 0.00350 -0.0941 0.1543 0.0484
3.500 0.9359 0.01274 0.00363 -0.0940 0.1507 0.1107
3.750 0.9645 0.01254 0.00385 -0.0944 0.1455 0.3704
4.000 0.9887 0.01176 0.00417 -0.0939 0.1399 0.8467
4.500 1.0355 0.01201 0.00443 -0.0916 0.1218 1.0000
4.750 1.0615 0.01234 0.00465 -0.0913 0.1118 1.0000
5.000 1.0877 0.01264 0.00488 -0.0909 0.1041 1.0000
5.250 1.1136 0.01295 0.00514 -0.0905 0.0978 1.0000
5.500 1.1397 0.01324 0.00539 -0.0901 0.0910 1.0000
5.750 1.1652 0.01359 0.00568 -0.0897 0.0854 1.0000
6.000 1.1911 0.01389 0.00595 -0.0893 0.0833 1.0000
6.250 1.2168 0.01419 0.00625 -0.0889 0.0814 1.0000
6.500 1.2424 0.01449 0.00653 -0.0885 0.0798 1.0000
6.750 1.2680 0.01479 0.00682 -0.0881 0.0784 1.0000
7.000 1.2935 0.01509 0.00712 -0.0877 0.0772 1.0000
7.250 1.3189 0.01538 0.00744 -0.0873 0.0765 1.0000
7.500 1.3441 0.01568 0.00775 -0.0869 0.0760 1.0000
7.750 1.3692 0.01599 0.00808 -0.0864 0.0755 1.0000
8.000 1.3941 0.01630 0.00842 -0.0860 0.0749 1.0000
8.250 1.4188 0.01663 0.00879 -0.0855 0.0743 1.0000
8.500 1.4432 0.01698 0.00917 -0.0850 0.0738 1.0000
8.750 1.4673 0.01734 0.00956 -0.0844 0.0732 1.0000
9.000 1.4913 0.01771 0.00997 -0.0839 0.0726 1.0000
9.250 1.5149 0.01810 0.01040 -0.0833 0.0721 1.0000
9.500 1.5383 0.01849 0.01084 -0.0827 0.0717 1.0000
9.750 1.5614 0.01890 0.01129 -0.0820 0.0713 1.0000
10.000 1.5840 0.01934 0.01179 -0.0813 0.0707 1.0000
10.250 1.6059 0.01984 0.01233 -0.0806 0.0697 1.0000
10.500 1.6272 0.02037 0.01291 -0.0797 0.0686 1.0000
10.750 1.6481 0.02090 0.01349 -0.0788 0.0676 1.0000
11.000 1.6693 0.02138 0.01404 -0.0780 0.0671 1.0000
11.250 1.6907 0.02180 0.01454 -0.0772 0.0666 1.0000
11.500 1.7114 0.02227 0.01509 -0.0763 0.0662 1.0000
11.750 1.7314 0.02276 0.01566 -0.0753 0.0658 1.0000
12.000 1.7507 0.02328 0.01627 -0.0742 0.0653 1.0000
12.250 1.7692 0.02383 0.01691 -0.0730 0.0647 1.0000
12.500 1.7868 0.02440 0.01757 -0.0717 0.0640 1.0000
12.750 1.8027 0.02500 0.01827 -0.0702 0.0631 1.0000
13.000 1.8162 0.02564 0.01900 -0.0683 0.0621 1.0000
13.250 1.8283 0.02633 0.01978 -0.0662 0.0610 1.0000
13.500 1.8393 0.02710 0.02065 -0.0642 0.0596 1.0000
13.750 1.8494 0.02794 0.02158 -0.0621 0.0585 1.0000
14.000 1.8590 0.02884 0.02260 -0.0601 0.0572 1.0000
14.250 1.8676 0.02985 0.02372 -0.0582 0.0551 1.0000
14.500 1.8745 0.03104 0.02499 -0.0563 0.0516 1.0000
14.750 1.8786 0.03251 0.02651 -0.0545 0.0505 1.0000
15.000 1.8798 0.03433 0.02836 -0.0528 0.0488 1.0000
15.250 1.8780 0.03654 0.03063 -0.0513 0.0469 1.0000
15.500 1.8749 0.03909 0.03328 -0.0503 0.0459 1.0000
15.750 1.8695 0.04213 0.03644 -0.0498 0.0453 1.0000
16.000 1.8610 0.04587 0.04032 -0.0501 0.0447 1.0000
16.250 1.8493 0.05044 0.04504 -0.0511 0.0442 1.0000
16.500 1.8341 0.05595 0.05071 -0.0530 0.0437 1.0000
16.750 1.8150 0.06245 0.05739 -0.0558 0.0434 1.0000
17.000 1.7921 0.06993 0.06505 -0.0592 0.0433 1.0000
17.250 1.7658 0.07823 0.07355 -0.0632 0.0432 1.0000
17.500 1.7369 0.08718 0.08268 -0.0675 0.0433 1.0000
17.750 1.7064 0.09667 0.09236 -0.0723 0.0433 1.0000
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