WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il) Reynolds number: 200,000 Max Cl/Cd: 76.95 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx72150b-il-200000-n5.txt Download as CSV file: xf-fx72150b-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 72-MS-150B AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 0.2506 0.10645 0.10118 -0.1488 0.7292 0.0227
-10.750 0.2562 0.10434 0.09903 -0.1502 0.7253 0.0228
-10.500 0.2622 0.10230 0.09700 -0.1515 0.7206 0.0229
-10.250 0.2706 0.09982 0.09451 -0.1523 0.7160 0.0230
-10.000 0.2832 0.09706 0.09170 -0.1526 0.7118 0.0232
-9.750 0.2933 0.09481 0.08941 -0.1532 0.7079 0.0236
-9.500 0.3021 0.09269 0.08729 -0.1539 0.7033 0.0239
-9.250 0.3108 0.09055 0.08515 -0.1547 0.6990 0.0246
-9.000 0.3192 0.08845 0.08302 -0.1555 0.6950 0.0249
-8.750 0.3272 0.08636 0.08090 -0.1563 0.6914 0.0256
-8.500 0.3340 0.08427 0.07882 -0.1573 0.6872 0.0264
-8.250 0.3377 0.08232 0.07688 -0.1586 0.6833 0.0268
-8.000 0.3428 0.08039 0.07493 -0.1597 0.6796 0.0269
-7.750 0.3443 0.07836 0.07289 -0.1613 0.6764 0.0270
-7.500 0.3606 0.07582 0.07036 -0.1604 0.6724 0.0275
-7.250 0.3714 0.07400 0.06853 -0.1604 0.6685 0.0284
-7.000 0.3792 0.07220 0.06671 -0.1609 0.6649 0.0298
-6.750 0.3812 0.07033 0.06483 -0.1620 0.6616 0.0314
-6.500 0.3794 0.06855 0.06309 -0.1628 0.6582 0.0316
-6.250 0.3798 0.06665 0.06125 -0.1641 0.6545 0.0318
-6.000 0.3895 0.06446 0.05907 -0.1638 0.6511 0.0320
-5.750 0.4007 0.06265 0.05723 -0.1633 0.6480 0.0324
-5.500 0.4116 0.06082 0.05537 -0.1639 0.6453 0.0330
-5.250 0.4222 0.05886 0.05341 -0.1653 0.6424 0.0337
-5.000 0.4335 0.05677 0.05135 -0.1673 0.6392 0.0343
-4.750 0.4475 0.05433 0.04892 -0.1705 0.6360 0.0353
-4.500 0.4842 0.04803 0.04253 -0.1873 0.6330 0.0371
-4.000 0.5536 0.03607 0.03015 -0.2057 0.6285 0.0226
-3.750 0.5972 0.03181 0.02560 -0.2147 0.6259 0.0221
-3.500 0.6537 0.02648 0.01959 -0.2257 0.6232 0.0232
-3.250 0.6918 0.02448 0.01725 -0.2297 0.6205 0.0236
-3.000 0.7348 0.02193 0.01407 -0.2343 0.6181 0.0233
-2.750 0.7693 0.02075 0.01257 -0.2364 0.6158 0.0235
-2.500 0.8024 0.01987 0.01142 -0.2380 0.6138 0.0240
-2.000 0.8651 0.01859 0.00976 -0.2402 0.6096 0.0256
-1.750 0.8946 0.01818 0.00925 -0.2409 0.6072 0.0276
-1.500 0.9237 0.01793 0.00898 -0.2416 0.6047 0.0298
-1.250 0.9537 0.01763 0.00860 -0.2424 0.6023 0.0315
-1.000 0.9842 0.01738 0.00833 -0.2434 0.6001 0.0337
-0.750 1.0147 0.01725 0.00812 -0.2443 0.5983 0.0377
-0.500 1.0455 0.01718 0.00799 -0.2452 0.5966 0.0440
-0.250 1.0757 0.01713 0.00790 -0.2461 0.5949 0.0548
0.000 1.1048 0.01706 0.00794 -0.2469 0.5929 0.0880
0.250 1.1372 0.01666 0.00815 -0.2488 0.5909 0.3245
0.500 1.1642 0.01677 0.00855 -0.2490 0.5889 0.4885
0.750 1.1901 0.01702 0.00882 -0.2489 0.5870 0.5357
1.000 1.2158 0.01727 0.00907 -0.2486 0.5850 0.5725
1.250 1.2417 0.01747 0.00926 -0.2484 0.5831 0.5960
1.500 1.2695 0.01765 0.00933 -0.2486 0.5813 0.6069
1.750 1.2977 0.01780 0.00942 -0.2490 0.5798 0.6133
2.000 1.3222 0.01805 0.00967 -0.2488 0.5778 0.6201
2.250 1.3466 0.01831 0.00994 -0.2486 0.5760 0.6261
2.500 1.3713 0.01856 0.01021 -0.2484 0.5742 0.6308
2.750 1.3964 0.01881 0.01047 -0.2483 0.5725 0.6362
3.000 1.4218 0.01906 0.01071 -0.2483 0.5708 0.6418
3.250 1.4473 0.01929 0.01094 -0.2483 0.5691 0.6473
3.500 1.4734 0.01951 0.01117 -0.2484 0.5676 0.6544
3.750 1.5000 0.01973 0.01137 -0.2485 0.5661 0.6610
4.000 1.5275 0.01994 0.01157 -0.2489 0.5648 0.6681
4.250 1.5543 0.02020 0.01182 -0.2491 0.5636 0.6757
4.500 1.5742 0.02060 0.01234 -0.2482 0.5620 0.6837
4.750 1.5944 0.02101 0.01282 -0.2474 0.5603 0.6933
5.000 1.6149 0.02140 0.01330 -0.2466 0.5586 0.7048
5.250 1.6356 0.02178 0.01376 -0.2458 0.5570 0.7183
5.500 1.6567 0.02214 0.01422 -0.2451 0.5555 0.7351
5.750 1.6779 0.02245 0.01464 -0.2444 0.5540 0.7600
6.000 1.6952 0.02255 0.01496 -0.2428 0.5526 0.9145
6.250 1.7199 0.02291 0.01533 -0.2428 0.5514 1.0000
6.500 1.7457 0.02323 0.01567 -0.2430 0.5501 1.0000
6.750 1.7734 0.02352 0.01595 -0.2435 0.5488 1.0000
7.000 1.7912 0.02407 0.01658 -0.2424 0.5470 1.0000
7.250 1.7902 0.02502 0.01767 -0.2381 0.5444 1.0000
7.500 1.7943 0.02592 0.01870 -0.2348 0.5419 1.0000
7.750 1.8041 0.02676 0.01962 -0.2326 0.5398 1.0000
8.000 1.8178 0.02748 0.02042 -0.2310 0.5379 1.0000
8.250 1.8366 0.02802 0.02102 -0.2301 0.5362 1.0000
8.500 1.8600 0.02838 0.02143 -0.2299 0.5346 1.0000
8.750 1.8882 0.02857 0.02166 -0.2304 0.5331 1.0000
9.000 1.9062 0.02916 0.02233 -0.2295 0.5312 1.0000
9.250 1.8414 0.03369 0.02714 -0.2181 0.5244 1.0000
9.500 1.8442 0.03525 0.02879 -0.2156 0.5213 1.0000
9.750 1.8632 0.03584 0.02947 -0.2150 0.5194 1.0000
10.000 1.8941 0.03561 0.02929 -0.2156 0.5177 1.0000
10.250 1.7872 0.04570 0.03964 -0.2033 0.5059 1.0000
10.500 1.8109 0.04581 0.03983 -0.2031 0.5039 1.0000
10.750 1.8518 0.04431 0.03837 -0.2042 0.5025 1.0000
11.000 1.9065 0.04163 0.03570 -0.2065 0.5008 1.0000
11.250 1.6189 0.07560 0.07001 -0.1882 0.4608 1.0000
11.500 1.6411 0.07561 0.07010 -0.1878 0.4588 1.0000
11.750 1.6700 0.07469 0.06925 -0.1877 0.4575 1.0000
12.000 1.7072 0.07255 0.06719 -0.1878 0.4565 1.0000
12.250 1.7473 0.07015 0.06485 -0.1880 0.4554 1.0000
13.250 1.6959 0.08919 0.08430 -0.1829 0.4141 1.0000
13.750 1.7297 0.09037 0.08559 -0.1819 0.3945 1.0000
14.000 1.7211 0.09479 0.09008 -0.1811 0.3776 1.0000
14.250 1.7807 0.08873 0.08377 -0.1810 0.3510 1.0000
14.500 1.7953 0.08935 0.08417 -0.1802 0.3235 1.0000
15.000 1.7780 0.09757 0.09198 -0.1781 0.2641 1.0000
15.250 1.7618 0.10297 0.09720 -0.1773 0.2345 1.0000
15.500 1.7451 0.10858 0.10264 -0.1767 0.2071 1.0000
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