KENNEDY AND MARSDEN AIRFOIL (kenmar-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: KENNEDY AND MARSDEN AIRFOIL (kenmar-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.86 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kenmar-il-1000000-n5.txt Download as CSV file: xf-kenmar-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.2074 0.08298 0.07701 -0.1572 0.4301 0.0353
-16.250 -0.2390 0.07533 0.06923 -0.1620 0.4300 0.0354
-16.000 -0.2551 0.06993 0.06374 -0.1655 0.4299 0.0356
-15.750 -0.2644 0.06549 0.05923 -0.1684 0.4298 0.0357
-15.500 -0.2705 0.06151 0.05519 -0.1710 0.4296 0.0358
-15.250 -0.2743 0.05788 0.05150 -0.1734 0.4294 0.0359
-15.000 -0.2762 0.05452 0.04808 -0.1757 0.4292 0.0360
-14.750 -0.2762 0.05145 0.04496 -0.1777 0.4289 0.0361
-14.500 -0.2746 0.04864 0.04209 -0.1795 0.4287 0.0362
-14.250 -0.2717 0.04603 0.03942 -0.1812 0.4283 0.0362
-14.000 -0.2667 0.04373 0.03707 -0.1826 0.4280 0.0363
-13.750 -0.2605 0.04164 0.03493 -0.1837 0.4276 0.0364
-13.500 -0.2536 0.03969 0.03293 -0.1848 0.4272 0.0364
-13.250 -0.2458 0.03790 0.03110 -0.1856 0.4269 0.0365
-13.000 -0.2371 0.03629 0.02945 -0.1863 0.4265 0.0366
-12.750 -0.2271 0.03484 0.02796 -0.1868 0.4262 0.0366
-12.500 -0.2172 0.03346 0.02655 -0.1872 0.4259 0.0367
-12.250 -0.2060 0.03225 0.02531 -0.1873 0.4255 0.0368
-12.000 -0.1950 0.03109 0.02412 -0.1874 0.4252 0.0369
-11.750 -0.1826 0.03009 0.02308 -0.1873 0.4248 0.0370
-11.500 -0.1710 0.02909 0.02205 -0.1872 0.4245 0.0371
-11.250 -0.1580 0.02824 0.02118 -0.1869 0.4241 0.0371
-11.000 -0.1460 0.02740 0.02031 -0.1864 0.4238 0.0372
-10.750 -0.1330 0.02667 0.01956 -0.1859 0.4234 0.0373
-10.500 -0.1200 0.02598 0.01885 -0.1852 0.4231 0.0374
-10.250 -0.1081 0.02527 0.01812 -0.1843 0.4230 0.0375
-10.000 -0.0954 0.02464 0.01748 -0.1833 0.4230 0.0376
-9.750 -0.0830 0.02405 0.01688 -0.1822 0.4229 0.0377
-9.500 -0.0718 0.02346 0.01627 -0.1809 0.4228 0.0378
-9.250 -0.0601 0.02293 0.01573 -0.1794 0.4227 0.0379
-9.000 -0.0492 0.02244 0.01523 -0.1777 0.4226 0.0380
-8.750 -0.0403 0.02194 0.01472 -0.1757 0.4225 0.0381
-8.500 -0.0324 0.02149 0.01427 -0.1733 0.4224 0.0382
-8.250 -0.0272 0.02107 0.01384 -0.1704 0.4223 0.0383
-8.000 -0.0311 0.02066 0.01344 -0.1659 0.4223 0.0384
-7.750 -0.0391 0.02025 0.01303 -0.1605 0.4222 0.0385
-7.500 -0.0327 0.01980 0.01258 -0.1578 0.4220 0.0386
-7.250 -0.0197 0.01938 0.01215 -0.1561 0.4219 0.0387
-7.000 -0.0035 0.01896 0.01173 -0.1550 0.4218 0.0388
-6.750 0.0162 0.01857 0.01132 -0.1545 0.4216 0.0390
-6.500 0.0384 0.01819 0.01093 -0.1543 0.4215 0.0391
-6.250 0.0629 0.01784 0.01057 -0.1545 0.4213 0.0392
-6.000 0.0892 0.01752 0.01023 -0.1550 0.4211 0.0394
-5.750 0.1171 0.01722 0.00992 -0.1557 0.4209 0.0395
-5.500 0.1463 0.01693 0.00963 -0.1566 0.4208 0.0396
-5.250 0.1765 0.01668 0.00936 -0.1576 0.4205 0.0397
-5.000 0.2082 0.01638 0.00905 -0.1590 0.4203 0.0400
-4.750 0.2412 0.01607 0.00874 -0.1607 0.4201 0.0404
-4.500 0.2744 0.01584 0.00851 -0.1622 0.4199 0.0408
-4.250 0.3076 0.01565 0.00833 -0.1637 0.4197 0.0412
-4.000 0.3406 0.01551 0.00820 -0.1650 0.4195 0.0416
-3.750 0.3737 0.01538 0.00807 -0.1663 0.4192 0.0420
-3.500 0.4070 0.01526 0.00795 -0.1676 0.4190 0.0423
-3.250 0.4403 0.01516 0.00784 -0.1689 0.4187 0.0426
-3.000 0.4736 0.01506 0.00775 -0.1702 0.4184 0.0431
-2.750 0.5070 0.01497 0.00766 -0.1715 0.4180 0.0434
-2.500 0.5406 0.01490 0.00759 -0.1728 0.4177 0.0438
-2.250 0.5743 0.01486 0.00754 -0.1741 0.4175 0.0442
-2.000 0.6080 0.01483 0.00752 -0.1754 0.4172 0.0446
-1.750 0.6430 0.01477 0.00747 -0.1770 0.4170 0.0453
-1.500 0.6774 0.01474 0.00745 -0.1785 0.4167 0.0460
-1.250 0.7118 0.01473 0.00746 -0.1799 0.4164 0.0469
-1.000 0.7458 0.01473 0.00747 -0.1813 0.4162 0.0478
-0.750 0.7796 0.01474 0.00749 -0.1826 0.4159 0.0489
-0.500 0.8130 0.01475 0.00750 -0.1839 0.4156 0.0497
-0.250 0.8472 0.01474 0.00752 -0.1853 0.4152 0.0515
0.000 0.8808 0.01474 0.00753 -0.1866 0.4148 0.0535
0.500 0.9477 0.01476 0.00759 -0.1891 0.4140 0.0592
0.750 0.9815 0.01479 0.00764 -0.1905 0.4137 0.0635
1.000 1.0159 0.01482 0.00770 -0.1920 0.4134 0.0707
1.250 1.0521 0.01484 0.00778 -0.1939 0.4131 0.0857
1.500 1.0916 0.01482 0.00787 -0.1965 0.4129 0.1184
1.750 1.1326 0.01479 0.00798 -0.1995 0.4126 0.1596
2.000 1.1752 0.01476 0.00810 -0.2028 0.4123 0.2106
2.250 1.2167 0.01477 0.00823 -0.2059 0.4121 0.2603
2.500 1.2609 0.01475 0.00838 -0.2096 0.4118 0.3209
2.750 1.3362 0.01454 0.00862 -0.2200 0.4115 0.5135
3.000 1.3727 0.01464 0.00885 -0.2219 0.4111 0.5691
3.250 1.4019 0.01481 0.00906 -0.2222 0.4108 0.5942
3.500 1.4289 0.01498 0.00924 -0.2222 0.4104 0.6067
3.750 1.4558 0.01515 0.00941 -0.2221 0.4100 0.6119
4.000 1.4819 0.01535 0.00962 -0.2220 0.4096 0.6174
4.250 1.5080 0.01558 0.00985 -0.2218 0.4092 0.6221
4.500 1.5341 0.01582 0.01010 -0.2217 0.4088 0.6267
4.750 1.5602 0.01610 0.01037 -0.2216 0.4083 0.6313
5.000 1.5866 0.01642 0.01068 -0.2215 0.4078 0.6350
5.250 1.6122 0.01668 0.01097 -0.2214 0.4074 0.6379
5.500 1.6370 0.01687 0.01118 -0.2210 0.4073 0.6395
5.750 1.6615 0.01706 0.01140 -0.2207 0.4071 0.6410
6.000 1.6857 0.01727 0.01162 -0.2203 0.4070 0.6426
6.250 1.7096 0.01748 0.01186 -0.2198 0.4068 0.6444
6.500 1.7328 0.01771 0.01211 -0.2193 0.4066 0.6460
6.750 1.7556 0.01794 0.01237 -0.2187 0.4064 0.6475
7.000 1.7782 0.01818 0.01263 -0.2181 0.4061 0.6489
7.250 1.8007 0.01844 0.01291 -0.2175 0.4059 0.6503
7.500 1.8230 0.01870 0.01320 -0.2169 0.4056 0.6516
7.750 1.8447 0.01897 0.01350 -0.2162 0.4053 0.6528
8.000 1.8656 0.01927 0.01383 -0.2154 0.4049 0.6540
8.250 1.8864 0.01957 0.01416 -0.2146 0.4046 0.6552
8.500 1.9071 0.01989 0.01450 -0.2138 0.4042 0.6563
8.750 1.9269 0.02024 0.01487 -0.2129 0.4038 0.6571
9.000 1.9466 0.02058 0.01526 -0.2120 0.4034 0.6587
9.250 1.9661 0.02094 0.01565 -0.2112 0.4030 0.6603
9.500 1.9849 0.02131 0.01607 -0.2102 0.4025 0.6618
9.750 2.0032 0.02170 0.01650 -0.2092 0.4020 0.6632
10.000 2.0217 0.02209 0.01692 -0.2083 0.4014 0.6645
10.250 2.0391 0.02251 0.01739 -0.2072 0.4009 0.6659
10.500 2.0565 0.02296 0.01787 -0.2062 0.4004 0.6672
10.750 2.0735 0.02344 0.01839 -0.2052 0.3999 0.6685
11.000 2.0897 0.02396 0.01895 -0.2041 0.3994 0.6698
11.250 2.1062 0.02449 0.01951 -0.2032 0.3989 0.6713
11.500 2.1214 0.02508 0.02014 -0.2021 0.3984 0.6729
11.750 2.1368 0.02568 0.02077 -0.2011 0.3979 0.6743
12.000 2.1508 0.02636 0.02149 -0.2000 0.3974 0.6756
12.250 2.1649 0.02708 0.02224 -0.1990 0.3968 0.6767
12.500 2.1778 0.02789 0.02309 -0.1979 0.3963 0.6777
12.750 2.1911 0.02871 0.02395 -0.1970 0.3957 0.6787
13.000 2.2027 0.02967 0.02494 -0.1959 0.3949 0.6796
13.250 2.2147 0.03064 0.02593 -0.1950 0.3941 0.6804
13.500 2.2212 0.03202 0.02737 -0.1937 0.3931 0.6811
13.750 2.2197 0.03409 0.02955 -0.1921 0.3923 0.6824
14.000 2.2139 0.03667 0.03225 -0.1906 0.3909 0.6838
14.250 2.2035 0.03982 0.03552 -0.1892 0.3891 0.6851
14.500 2.1795 0.04442 0.04026 -0.1876 0.3866 0.6861
14.750 2.1339 0.05146 0.04743 -0.1859 0.3830 0.6869
15.250 1.6476 0.10756 0.10396 -0.1743 0.3396 0.6824
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