EPPLER 1211 AIRFOIL (e1211-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1211 AIRFOIL (e1211-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.1 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1211-il-1000000-n5.txt Download as CSV file: xf-e1211-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1211 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
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7512 0.08793 0.08454 -0.0526 1.0000 0.0170
-15.750 -0.7656 0.08259 0.07913 -0.0554 1.0000 0.0171
-15.500 -0.7828 0.07703 0.07351 -0.0583 1.0000 0.0172
-15.250 -0.8059 0.07087 0.06727 -0.0617 1.0000 0.0173
-15.000 -0.8420 0.06350 0.05980 -0.0659 1.0000 0.0172
-14.750 -0.9075 0.05300 0.04912 -0.0721 1.0000 0.0170
-14.500 -1.0254 0.03644 0.03221 -0.0815 1.0000 0.0165
-13.750 -1.0190 0.02234 0.01756 -0.0984 0.9867 0.0170
-13.500 -0.9947 0.02120 0.01637 -0.0995 0.9804 0.0172
-13.000 -0.9432 0.01930 0.01436 -0.1011 0.9454 0.0179
-12.750 -0.8672 0.01813 0.01307 -0.1115 0.9191 0.0186
-12.500 -0.8345 0.01760 0.01226 -0.1131 0.8550 0.0190
-12.250 -0.8176 0.01711 0.01158 -0.1115 0.8152 0.0197
-12.000 -0.7984 0.01665 0.01099 -0.1104 0.7864 0.0204
-11.750 -0.7776 0.01621 0.01044 -0.1093 0.7628 0.0211
-11.250 -0.7336 0.01535 0.00939 -0.1076 0.7247 0.0232
-11.000 -0.7106 0.01495 0.00889 -0.1069 0.7073 0.0249
-10.750 -0.6872 0.01449 0.00838 -0.1062 0.6917 0.0274
-10.500 -0.6638 0.01401 0.00786 -0.1056 0.6779 0.0317
-10.250 -0.6399 0.01358 0.00737 -0.1049 0.6634 0.0368
-10.000 -0.6153 0.01314 0.00692 -0.1044 0.6502 0.0426
-9.750 -0.5901 0.01278 0.00652 -0.1039 0.6381 0.0479
-9.500 -0.5645 0.01245 0.00615 -0.1034 0.6251 0.0531
-9.250 -0.5384 0.01214 0.00581 -0.1030 0.6140 0.0583
-9.000 -0.5121 0.01186 0.00550 -0.1026 0.6025 0.0634
-8.750 -0.4854 0.01159 0.00522 -0.1022 0.5920 0.0687
-8.500 -0.4586 0.01137 0.00495 -0.1019 0.5802 0.0740
-8.250 -0.4313 0.01113 0.00470 -0.1016 0.5711 0.0799
-8.000 -0.4042 0.01093 0.00447 -0.1012 0.5604 0.0860
-7.750 -0.3768 0.01071 0.00425 -0.1009 0.5510 0.0925
-7.500 -0.3493 0.01054 0.00405 -0.1006 0.5411 0.0983
-7.250 -0.3213 0.01041 0.00389 -0.1004 0.5326 0.1034
-7.000 -0.2934 0.01025 0.00373 -0.1001 0.5229 0.1085
-6.750 -0.2653 0.01016 0.00359 -0.0998 0.5141 0.1129
-6.500 -0.2371 0.01002 0.00345 -0.0996 0.5059 0.1180
-6.000 -0.1805 0.00985 0.00322 -0.0991 0.4889 0.1273
-5.750 -0.1521 0.00979 0.00312 -0.0989 0.4804 0.1315
-5.500 -0.1236 0.00972 0.00303 -0.0987 0.4735 0.1357
-5.250 -0.0951 0.00965 0.00295 -0.0985 0.4659 0.1400
-5.000 -0.0667 0.00963 0.00288 -0.0983 0.4571 0.1439
-4.750 -0.0379 0.00957 0.00280 -0.0981 0.4506 0.1476
-4.500 -0.0093 0.00952 0.00274 -0.0979 0.4436 0.1511
-4.250 0.0192 0.00951 0.00268 -0.0977 0.4364 0.1541
-4.000 0.0481 0.00949 0.00263 -0.0975 0.4302 0.1565
-3.750 0.0767 0.00947 0.00257 -0.0973 0.4225 0.1592
-3.500 0.1052 0.00945 0.00253 -0.0971 0.4157 0.1625
-3.250 0.1341 0.00942 0.00250 -0.0970 0.4103 0.1654
-3.000 0.1627 0.00943 0.00246 -0.0968 0.4038 0.1680
-2.750 0.1913 0.00945 0.00244 -0.0966 0.3971 0.1701
-2.500 0.2201 0.00943 0.00240 -0.0964 0.3912 0.1726
-2.250 0.2486 0.00943 0.00239 -0.0962 0.3847 0.1760
-2.000 0.2770 0.00945 0.00238 -0.0960 0.3788 0.1790
-1.750 0.3059 0.00945 0.00237 -0.0959 0.3743 0.1815
-1.500 0.3345 0.00948 0.00237 -0.0957 0.3684 0.1839
-1.250 0.3628 0.00953 0.00237 -0.0955 0.3616 0.1860
-1.000 0.3914 0.00953 0.00237 -0.0953 0.3571 0.1894
-0.750 0.4200 0.00954 0.00238 -0.0952 0.3523 0.1928
-0.500 0.4483 0.00959 0.00240 -0.0950 0.3469 0.1961
-0.250 0.4766 0.00964 0.00243 -0.0947 0.3415 0.1987
0.000 0.5052 0.00968 0.00245 -0.0946 0.3371 0.2007
0.250 0.5335 0.00971 0.00248 -0.0944 0.3321 0.2048
0.500 0.5615 0.00976 0.00252 -0.0942 0.3272 0.2087
0.750 0.5897 0.00981 0.00256 -0.0939 0.3230 0.2121
1.000 0.6181 0.00986 0.00260 -0.0938 0.3188 0.2154
1.250 0.6462 0.00993 0.00265 -0.0935 0.3140 0.2185
1.500 0.6739 0.01000 0.00272 -0.0933 0.3095 0.2239
1.750 0.7019 0.01005 0.00278 -0.0931 0.3060 0.2285
2.000 0.7301 0.01011 0.00284 -0.0929 0.3027 0.2329
2.500 0.7854 0.01026 0.00299 -0.0924 0.2939 0.2446
2.750 0.8128 0.01035 0.00309 -0.0921 0.2898 0.2514
3.000 0.8407 0.01041 0.00316 -0.0919 0.2873 0.2579
3.250 0.8684 0.01047 0.00325 -0.0916 0.2842 0.2669
3.500 0.8957 0.01056 0.00335 -0.0914 0.2805 0.2751
3.750 0.9226 0.01066 0.00347 -0.0910 0.2765 0.2880
4.000 0.9496 0.01076 0.00359 -0.0907 0.2729 0.3022
4.500 1.0040 0.01089 0.00382 -0.0902 0.2673 0.3368
4.750 1.0307 0.01097 0.00395 -0.0898 0.2642 0.3578
5.000 1.0571 0.01108 0.00410 -0.0895 0.2610 0.3828
5.250 1.0831 0.01117 0.00427 -0.0890 0.2574 0.4164
5.500 1.1098 0.01122 0.00442 -0.0887 0.2552 0.4542
5.750 1.1361 0.01128 0.00457 -0.0884 0.2523 0.4943
6.000 1.1620 0.01134 0.00475 -0.0880 0.2493 0.5403
6.250 1.1873 0.01141 0.00494 -0.0875 0.2463 0.5967
6.500 1.2120 0.01147 0.00516 -0.0868 0.2433 0.6713
6.750 1.2361 0.01146 0.00538 -0.0861 0.2410 0.7609
7.000 1.2540 0.01128 0.00558 -0.0839 0.2393 0.9052
7.250 1.2850 0.01138 0.00575 -0.0844 0.2366 1.0000
7.500 1.3097 0.01158 0.00594 -0.0838 0.2337 1.0000
7.750 1.3336 0.01182 0.00615 -0.0831 0.2306 1.0000
8.000 1.3569 0.01207 0.00637 -0.0823 0.2275 1.0000
8.250 1.3809 0.01227 0.00658 -0.0815 0.2256 1.0000
8.500 1.4047 0.01246 0.00678 -0.0808 0.2238 1.0000
8.750 1.4279 0.01267 0.00700 -0.0800 0.2216 1.0000
9.000 1.4504 0.01291 0.00724 -0.0790 0.2193 1.0000
9.250 1.4708 0.01316 0.00749 -0.0777 0.2168 1.0000
9.500 1.4891 0.01345 0.00777 -0.0761 0.2139 1.0000
9.750 1.5076 0.01373 0.00805 -0.0745 0.2117 1.0000
10.000 1.5271 0.01397 0.00831 -0.0730 0.2101 1.0000
10.250 1.5463 0.01423 0.00859 -0.0716 0.2083 1.0000
10.500 1.5646 0.01453 0.00891 -0.0701 0.2063 1.0000
10.750 1.5819 0.01487 0.00925 -0.0685 0.2041 1.0000
11.000 1.5981 0.01526 0.00964 -0.0667 0.2016 1.0000
11.250 1.6131 0.01569 0.01009 -0.0649 0.1991 1.0000
11.500 1.6294 0.01609 0.01051 -0.0633 0.1974 1.0000
11.750 1.6461 0.01648 0.01093 -0.0618 0.1958 1.0000
12.000 1.6616 0.01693 0.01142 -0.0602 0.1937 1.0000
12.250 1.6757 0.01746 0.01197 -0.0586 0.1915 1.0000
12.500 1.6879 0.01810 0.01262 -0.0568 0.1889 1.0000
12.750 1.6984 0.01886 0.01339 -0.0549 0.1862 1.0000
13.000 1.7098 0.01962 0.01418 -0.0533 0.1842 1.0000
13.250 1.7231 0.02033 0.01493 -0.0520 0.1825 1.0000
13.500 1.7350 0.02115 0.01579 -0.0506 0.1804 1.0000
13.750 1.7455 0.02209 0.01677 -0.0493 0.1784 1.0000
14.000 1.7540 0.02321 0.01792 -0.0479 0.1761 1.0000
14.250 1.7608 0.02452 0.01925 -0.0466 0.1737 1.0000
14.500 1.7670 0.02593 0.02070 -0.0454 0.1717 1.0000
14.750 1.7770 0.02713 0.02196 -0.0445 0.1702 1.0000
15.000 1.7854 0.02850 0.02338 -0.0437 0.1685 1.0000
15.250 1.7921 0.03003 0.02496 -0.0429 0.1663 1.0000
15.500 1.7962 0.03184 0.02681 -0.0421 0.1640 1.0000
15.750 1.7982 0.03389 0.02890 -0.0414 0.1619 1.0000
16.000 1.7972 0.03627 0.03132 -0.0407 0.1594 1.0000
16.250 1.8023 0.03815 0.03327 -0.0403 0.1577 1.0000
16.500 1.8040 0.04041 0.03558 -0.0400 0.1551 1.0000
16.750 1.8024 0.04305 0.03827 -0.0397 0.1523 1.0000
17.000 1.7974 0.04612 0.04139 -0.0396 0.1498 1.0000
17.250 1.7917 0.04937 0.04469 -0.0396 0.1469 1.0000
17.500 1.7909 0.05215 0.04753 -0.0398 0.1444 1.0000
17.750 1.7841 0.05567 0.05111 -0.0401 0.1407 1.0000
18.000 1.7758 0.05947 0.05496 -0.0406 0.1384 1.0000
18.250 1.7654 0.06362 0.05917 -0.0413 0.1354 1.0000
18.500 1.7584 0.06745 0.06307 -0.0420 0.1323 1.0000
18.750 1.7489 0.07169 0.06737 -0.0430 0.1295 1.0000
19.000 1.7304 0.07717 0.07290 -0.0445 0.1260 1.0000
19.250 1.7253 0.08099 0.07679 -0.0455 0.1235 1.0000
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Polar data table (+)
Polar graphs
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