Marsden (marsden-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Marsden (marsden-il) Reynolds number: 500,000 Max Cl/Cd: 59.1 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-marsden-il-500000-n5.txt Download as CSV file: xf-marsden-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Marsden
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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.0718 0.06572 0.05865 -0.1699 0.4385 0.0399
-15.250 -0.0964 0.05925 0.05203 -0.1747 0.4385 0.0400
-15.000 -0.1083 0.05466 0.04733 -0.1780 0.4384 0.0401
-14.750 -0.1134 0.05113 0.04370 -0.1804 0.4382 0.0402
-14.500 -0.1146 0.04818 0.04067 -0.1823 0.4380 0.0403
-14.250 -0.1130 0.04567 0.03810 -0.1838 0.4379 0.0404
-14.000 -0.1095 0.04348 0.03585 -0.1850 0.4377 0.0405
-13.750 -0.1043 0.04156 0.03387 -0.1859 0.4374 0.0406
-13.500 -0.0978 0.03986 0.03212 -0.1866 0.4372 0.0407
-13.250 -0.0900 0.03834 0.03056 -0.1870 0.4370 0.0408
-13.000 -0.0819 0.03693 0.02912 -0.1873 0.4368 0.0409
-12.750 -0.0727 0.03569 0.02783 -0.1873 0.4365 0.0410
-12.500 -0.0631 0.03454 0.02665 -0.1873 0.4363 0.0411
-12.250 -0.0527 0.03351 0.02559 -0.1870 0.4360 0.0412
-12.000 -0.0422 0.03254 0.02458 -0.1867 0.4357 0.0413
-11.750 -0.0305 0.03167 0.02368 -0.1862 0.4355 0.0415
-11.500 -0.0191 0.03084 0.02281 -0.1856 0.4352 0.0416
-11.250 -0.0069 0.03007 0.02202 -0.1849 0.4349 0.0417
-11.000 0.0056 0.02937 0.02129 -0.1841 0.4347 0.0419
-10.750 0.0179 0.02869 0.02059 -0.1832 0.4344 0.0420
-10.500 0.0307 0.02808 0.01995 -0.1822 0.4341 0.0422
-10.250 0.0436 0.02750 0.01935 -0.1810 0.4338 0.0423
-10.000 0.0561 0.02695 0.01878 -0.1798 0.4335 0.0425
-9.750 0.0685 0.02643 0.01824 -0.1784 0.4333 0.0427
-9.500 0.0807 0.02596 0.01775 -0.1769 0.4330 0.0429
-9.250 0.0921 0.02551 0.01728 -0.1751 0.4327 0.0430
-9.000 0.1021 0.02509 0.01685 -0.1731 0.4324 0.0432
-8.750 0.1102 0.02473 0.01648 -0.1707 0.4322 0.0434
-8.500 0.1163 0.02442 0.01617 -0.1679 0.4319 0.0435
-8.250 0.1268 0.02408 0.01581 -0.1658 0.4317 0.0437
-8.000 0.1403 0.02374 0.01546 -0.1642 0.4314 0.0439
-7.750 0.1558 0.02341 0.01511 -0.1630 0.4311 0.0441
-7.500 0.1726 0.02308 0.01477 -0.1619 0.4308 0.0443
-7.250 0.1914 0.02278 0.01445 -0.1611 0.4305 0.0445
-7.000 0.2117 0.02250 0.01415 -0.1606 0.4303 0.0447
-6.750 0.2318 0.02210 0.01377 -0.1601 0.4300 0.0451
-6.500 0.2543 0.02176 0.01344 -0.1600 0.4296 0.0455
-6.250 0.2786 0.02148 0.01316 -0.1601 0.4293 0.0458
-6.000 0.3043 0.02122 0.01290 -0.1605 0.4289 0.0462
-5.750 0.3312 0.02098 0.01265 -0.1610 0.4285 0.0466
-5.500 0.3594 0.02076 0.01243 -0.1617 0.4282 0.0470
-5.250 0.3886 0.02058 0.01224 -0.1625 0.4279 0.0475
-5.000 0.4185 0.02042 0.01207 -0.1635 0.4276 0.0479
-4.750 0.4489 0.02028 0.01192 -0.1645 0.4273 0.0484
-4.500 0.4798 0.02016 0.01180 -0.1656 0.4270 0.0489
-4.250 0.5110 0.02008 0.01170 -0.1666 0.4267 0.0494
-4.000 0.5425 0.02002 0.01164 -0.1678 0.4264 0.0499
-3.750 0.5756 0.01992 0.01155 -0.1693 0.4261 0.0507
-3.500 0.6084 0.01989 0.01153 -0.1707 0.4258 0.0514
-3.250 0.6413 0.01991 0.01155 -0.1721 0.4255 0.0523
-3.000 0.6743 0.01995 0.01160 -0.1734 0.4251 0.0534
-2.750 0.7073 0.02005 0.01170 -0.1748 0.4246 0.0546
-2.500 0.7407 0.02023 0.01188 -0.1763 0.4240 0.0559
-2.250 0.7742 0.02052 0.01221 -0.1779 0.4232 0.0576
-2.000 0.8055 0.02054 0.01225 -0.1790 0.4231 0.0599
-1.750 0.8369 0.02056 0.01230 -0.1801 0.4228 0.0626
-1.500 0.8685 0.02058 0.01236 -0.1812 0.4226 0.0665
-1.250 0.9004 0.02062 0.01244 -0.1824 0.4223 0.0718
-1.000 0.9325 0.02066 0.01255 -0.1837 0.4220 0.0802
-0.750 0.9667 0.02072 0.01271 -0.1855 0.4217 0.0989
-0.500 1.0039 0.02076 0.01290 -0.1880 0.4215 0.1349
-0.250 1.0444 0.02079 0.01312 -0.1912 0.4211 0.1877
0.000 1.0856 0.02085 0.01339 -0.1946 0.4208 0.2454
0.250 1.1297 0.02094 0.01367 -0.1986 0.4204 0.3130
0.500 1.2039 0.02089 0.01414 -0.2090 0.4200 0.4886
0.750 1.2374 0.02116 0.01465 -0.2106 0.4196 0.5664
1.000 1.2604 0.02149 0.01505 -0.2099 0.4192 0.5929
1.250 1.2826 0.02183 0.01542 -0.2092 0.4187 0.6116
1.500 1.3007 0.02217 0.01582 -0.2076 0.4183 0.6217
1.750 1.3236 0.02248 0.01613 -0.2071 0.4177 0.6283
2.000 1.3480 0.02281 0.01644 -0.2069 0.4172 0.6332
2.250 1.3669 0.02315 0.01684 -0.2056 0.4167 0.6373
2.500 1.3856 0.02353 0.01726 -0.2043 0.4162 0.6416
2.750 1.4038 0.02394 0.01770 -0.2030 0.4158 0.6466
3.000 1.4231 0.02436 0.01813 -0.2020 0.4153 0.6516
3.250 1.4441 0.02477 0.01854 -0.2014 0.4149 0.6551
3.500 1.4655 0.02517 0.01894 -0.2009 0.4144 0.6568
3.750 1.4852 0.02556 0.01935 -0.2002 0.4140 0.6582
4.000 1.5037 0.02596 0.01979 -0.1992 0.4136 0.6597
4.250 1.5220 0.02637 0.02023 -0.1983 0.4131 0.6611
4.500 1.5393 0.02682 0.02070 -0.1972 0.4127 0.6626
4.750 1.5565 0.02727 0.02118 -0.1961 0.4123 0.6643
5.000 1.5739 0.02773 0.02166 -0.1951 0.4119 0.6658
5.250 1.5912 0.02821 0.02216 -0.1942 0.4115 0.6672
5.500 1.6088 0.02870 0.02267 -0.1934 0.4111 0.6687
5.750 1.6262 0.02921 0.02319 -0.1926 0.4107 0.6702
6.000 1.6438 0.02972 0.02372 -0.1919 0.4103 0.6717
6.250 1.6613 0.03027 0.02428 -0.1913 0.4099 0.6732
6.500 1.6789 0.03084 0.02486 -0.1907 0.4095 0.6749
6.750 1.6962 0.03144 0.02548 -0.1901 0.4090 0.6767
7.000 1.7130 0.03212 0.02616 -0.1895 0.4086 0.6782
7.250 1.7299 0.03285 0.02690 -0.1890 0.4080 0.6795
7.500 1.7194 0.03486 0.02902 -0.1858 0.4071 0.6805
8.000 1.0357 0.10945 0.10505 -0.1655 0.3510 0.6774
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