KENNEDY AND MARSDEN AIRFOIL (kenmar-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: KENNEDY AND MARSDEN AIRFOIL (kenmar-il) Reynolds number: 500,000 Max Cl/Cd: 59.01 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kenmar-il-500000-n5.txt Download as CSV file: xf-kenmar-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: KENNEDY AND MARSDEN 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.0817 0.06339 0.05626 -0.1718 0.4384 0.0400
-13.500 -0.1007 0.05772 0.05046 -0.1757 0.4383 0.0401
-13.250 -0.1095 0.05359 0.04623 -0.1785 0.4382 0.0402
-13.000 -0.1133 0.05024 0.04280 -0.1807 0.4380 0.0402
-12.750 -0.1137 0.04742 0.03990 -0.1825 0.4379 0.0403
-12.500 -0.1114 0.04503 0.03744 -0.1839 0.4377 0.0404
-12.250 -0.1075 0.04291 0.03527 -0.1849 0.4375 0.0405
-12.000 -0.1020 0.04104 0.03335 -0.1858 0.4373 0.0406
-11.750 -0.0951 0.03940 0.03166 -0.1864 0.4370 0.0407
-11.500 -0.0872 0.03791 0.03013 -0.1868 0.4368 0.0408
-11.250 -0.0787 0.03656 0.02873 -0.1870 0.4366 0.0409
-11.000 -0.0695 0.03534 0.02747 -0.1871 0.4363 0.0410
-10.750 -0.0596 0.03424 0.02634 -0.1870 0.4361 0.0411
-10.500 -0.0492 0.03322 0.02529 -0.1868 0.4358 0.0412
-10.250 -0.0383 0.03228 0.02431 -0.1864 0.4356 0.0414
-10.000 -0.0268 0.03142 0.02342 -0.1859 0.4353 0.0415
-9.750 -0.0152 0.03060 0.02257 -0.1854 0.4350 0.0416
-9.500 -0.0028 0.02986 0.02180 -0.1847 0.4347 0.0418
-9.250 0.0096 0.02916 0.02108 -0.1839 0.4345 0.0419
-9.000 0.0220 0.02850 0.02039 -0.1830 0.4342 0.0421
-8.750 0.0349 0.02790 0.01977 -0.1820 0.4339 0.0422
-8.500 0.0477 0.02733 0.01918 -0.1809 0.4336 0.0424
-8.250 0.0601 0.02679 0.01861 -0.1796 0.4333 0.0426
-8.000 0.0725 0.02629 0.01809 -0.1782 0.4331 0.0427
-7.750 0.0846 0.02582 0.01761 -0.1767 0.4328 0.0429
-7.500 0.0956 0.02538 0.01715 -0.1749 0.4325 0.0431
-7.250 0.1050 0.02497 0.01673 -0.1728 0.4323 0.0433
-7.000 0.1124 0.02463 0.01639 -0.1702 0.4320 0.0434
-6.750 0.1190 0.02433 0.01607 -0.1675 0.4317 0.0436
-6.500 0.1308 0.02398 0.01570 -0.1657 0.4315 0.0437
-6.250 0.1449 0.02364 0.01535 -0.1642 0.4312 0.0439
-6.000 0.1608 0.02331 0.01501 -0.1630 0.4309 0.0441
-5.750 0.1781 0.02299 0.01467 -0.1621 0.4306 0.0443
-5.500 0.1974 0.02270 0.01436 -0.1614 0.4304 0.0445
-5.250 0.2175 0.02237 0.01403 -0.1609 0.4301 0.0448
-5.000 0.2384 0.02200 0.01367 -0.1606 0.4298 0.0452
-4.750 0.2614 0.02168 0.01336 -0.1606 0.4294 0.0456
-4.500 0.2861 0.02140 0.01308 -0.1608 0.4290 0.0460
-4.250 0.3122 0.02114 0.01282 -0.1613 0.4287 0.0464
-4.000 0.3394 0.02091 0.01258 -0.1618 0.4283 0.0467
-3.750 0.3679 0.02070 0.01237 -0.1626 0.4280 0.0471
-3.500 0.3973 0.02052 0.01219 -0.1635 0.4277 0.0476
-3.250 0.4274 0.02037 0.01202 -0.1645 0.4274 0.0480
-3.000 0.4580 0.02024 0.01189 -0.1656 0.4271 0.0486
-2.750 0.4889 0.02013 0.01176 -0.1666 0.4268 0.0491
-2.500 0.5201 0.02006 0.01168 -0.1677 0.4265 0.0496
-2.250 0.5522 0.01997 0.01159 -0.1690 0.4262 0.0502
-2.000 0.5851 0.01990 0.01154 -0.1704 0.4259 0.0510
-1.750 0.6179 0.01988 0.01153 -0.1718 0.4256 0.0518
-1.500 0.6506 0.01991 0.01156 -0.1731 0.4253 0.0527
-1.250 0.6836 0.01997 0.01162 -0.1745 0.4249 0.0539
-1.000 0.7166 0.02008 0.01172 -0.1758 0.4244 0.0550
-0.750 0.7504 0.02026 0.01192 -0.1774 0.4237 0.0565
-0.500 0.7833 0.02052 0.01222 -0.1788 0.4231 0.0583
-0.250 0.8144 0.02055 0.01227 -0.1798 0.4229 0.0607
0.000 0.8461 0.02056 0.01231 -0.1809 0.4226 0.0638
0.250 0.8773 0.02060 0.01239 -0.1819 0.4224 0.0678
0.500 0.9094 0.02062 0.01247 -0.1831 0.4221 0.0741
0.750 0.9423 0.02068 0.01260 -0.1845 0.4218 0.0849
1.000 0.9775 0.02073 0.01276 -0.1864 0.4216 0.1097
1.250 1.0158 0.02077 0.01297 -0.1891 0.4213 0.1511
1.500 1.0570 0.02080 0.01321 -0.1924 0.4209 0.2077
1.750 1.0994 0.02087 0.01347 -0.1959 0.4206 0.2694
2.000 1.1495 0.02092 0.01378 -0.2011 0.4202 0.3546
2.250 1.2174 0.02096 0.01434 -0.2100 0.4198 0.5319
2.500 1.2439 0.02127 0.01479 -0.2100 0.4194 0.5762
2.750 1.2661 0.02161 0.01519 -0.2090 0.4190 0.5990
3.000 1.2869 0.02194 0.01556 -0.2079 0.4185 0.6147
3.250 1.3067 0.02229 0.01595 -0.2065 0.4181 0.6239
3.500 1.3301 0.02261 0.01626 -0.2060 0.4175 0.6300
3.750 1.3531 0.02293 0.01658 -0.2054 0.4170 0.6345
4.000 1.3718 0.02327 0.01697 -0.2040 0.4165 0.6385
4.250 1.3902 0.02366 0.01740 -0.2025 0.4160 0.6429
4.500 1.4084 0.02408 0.01785 -0.2011 0.4156 0.6481
4.750 1.4283 0.02450 0.01828 -0.2000 0.4151 0.6528
5.000 1.4494 0.02490 0.01869 -0.1993 0.4147 0.6556
5.250 1.4706 0.02531 0.01909 -0.1987 0.4142 0.6571
5.500 1.4896 0.02570 0.01951 -0.1976 0.4138 0.6586
5.750 1.5079 0.02611 0.01995 -0.1965 0.4133 0.6600
6.000 1.5257 0.02654 0.02041 -0.1953 0.4129 0.6615
6.250 1.5429 0.02699 0.02089 -0.1940 0.4125 0.6631
6.500 1.5601 0.02745 0.02137 -0.1928 0.4121 0.6647
6.750 1.5773 0.02792 0.02186 -0.1917 0.4116 0.6662
7.000 1.5946 0.02840 0.02237 -0.1906 0.4112 0.6676
7.250 1.6121 0.02890 0.02288 -0.1896 0.4108 0.6691
7.500 1.6292 0.02943 0.02342 -0.1886 0.4104 0.6706
7.750 1.6470 0.02994 0.02395 -0.1878 0.4100 0.6721
8.000 1.6642 0.03051 0.02453 -0.1869 0.4096 0.6736
8.250 1.6817 0.03108 0.02512 -0.1861 0.4092 0.6753
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Polar data table (+)
Polar graphs
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