E211 (10.96%) (e211-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E211 (10.96%) (e211-il) Reynolds number: 500,000 Max Cl/Cd: 91.68 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e211-il-500000-n5.txt Download as CSV file: xf-e211-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E211 (10.96%)
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6411 0.05374 0.05126 -0.0559 1.0000 0.0083
-10.000 -0.6702 0.04837 0.04578 -0.0582 1.0000 0.0083
-9.750 -0.6868 0.04278 0.03996 -0.0639 0.9968 0.0083
-9.500 -0.6784 0.03683 0.03354 -0.0702 0.9922 0.0083
-9.250 -0.6619 0.03285 0.02915 -0.0736 0.9883 0.0084
-9.000 -0.6366 0.03029 0.02621 -0.0764 0.9859 0.0086
-8.750 -0.6146 0.02718 0.02271 -0.0785 0.9833 0.0087
-8.500 -0.5956 0.02431 0.01950 -0.0791 0.9793 0.0089
-8.250 -0.5696 0.02224 0.01718 -0.0804 0.9767 0.0090
-8.000 -0.5404 0.02066 0.01539 -0.0818 0.9748 0.0092
-7.750 -0.5097 0.01932 0.01388 -0.0834 0.9734 0.0093
-7.500 -0.4832 0.01824 0.01267 -0.0838 0.9707 0.0095
-7.250 -0.4592 0.01729 0.01161 -0.0835 0.9666 0.0097
-7.000 -0.4300 0.01640 0.01061 -0.0843 0.9640 0.0099
-6.750 -0.3989 0.01558 0.00969 -0.0855 0.9620 0.0102
-6.500 -0.3665 0.01482 0.00883 -0.0868 0.9604 0.0106
-6.250 -0.3432 0.01417 0.00812 -0.0862 0.9554 0.0108
-6.000 -0.3151 0.01354 0.00742 -0.0865 0.9515 0.0112
-5.750 -0.2837 0.01294 0.00675 -0.0875 0.9489 0.0115
-5.500 -0.2506 0.01239 0.00615 -0.0888 0.9469 0.0119
-5.250 -0.2287 0.01204 0.00574 -0.0877 0.9393 0.0123
-5.000 -0.1980 0.01136 0.00500 -0.0885 0.9355 0.0131
-4.750 -0.1706 0.01093 0.00453 -0.0885 0.9296 0.0137
-4.500 -0.1417 0.01054 0.00409 -0.0888 0.9235 0.0145
-4.250 -0.1081 0.01016 0.00366 -0.0900 0.9193 0.0156
-4.000 -0.0776 0.00987 0.00331 -0.0906 0.9115 0.0168
-3.750 -0.0392 0.00947 0.00293 -0.0929 0.9066 0.0225
-3.500 -0.0022 0.00898 0.00260 -0.0951 0.8983 0.0602
-3.250 0.0388 0.00848 0.00229 -0.0983 0.8900 0.1154
-3.000 0.0780 0.00812 0.00204 -0.1009 0.8779 0.1602
-2.750 0.1139 0.00777 0.00182 -0.1029 0.8626 0.2185
-2.500 0.1459 0.00740 0.00164 -0.1041 0.8440 0.2960
-2.250 0.1749 0.00692 0.00150 -0.1047 0.8244 0.4208
-1.750 0.2303 0.00678 0.00147 -0.1047 0.7853 0.5300
-1.500 0.2572 0.00683 0.00145 -0.1044 0.7664 0.5484
-1.250 0.2839 0.00689 0.00144 -0.1040 0.7484 0.5654
-1.000 0.3104 0.00696 0.00145 -0.1037 0.7314 0.5798
-0.750 0.3370 0.00703 0.00145 -0.1034 0.7152 0.5920
-0.500 0.3635 0.00710 0.00147 -0.1030 0.6997 0.6037
-0.250 0.3900 0.00717 0.00149 -0.1027 0.6851 0.6145
0.000 0.4166 0.00724 0.00152 -0.1024 0.6708 0.6249
0.250 0.4433 0.00732 0.00156 -0.1021 0.6574 0.6354
0.500 0.4699 0.00739 0.00161 -0.1018 0.6443 0.6455
0.750 0.4965 0.00746 0.00166 -0.1015 0.6315 0.6554
1.000 0.5232 0.00754 0.00172 -0.1012 0.6189 0.6655
1.250 0.5496 0.00762 0.00179 -0.1009 0.6056 0.6747
1.500 0.5759 0.00772 0.00186 -0.1006 0.5912 0.6830
1.750 0.6021 0.00783 0.00194 -0.1002 0.5759 0.6914
2.000 0.6282 0.00793 0.00203 -0.0998 0.5610 0.6994
2.250 0.6545 0.00804 0.00212 -0.0995 0.5466 0.7083
2.500 0.6804 0.00815 0.00222 -0.0991 0.5310 0.7172
2.750 0.7061 0.00828 0.00233 -0.0987 0.5138 0.7266
3.000 0.7316 0.00843 0.00246 -0.0982 0.4958 0.7367
3.250 0.7569 0.00857 0.00259 -0.0977 0.4772 0.7478
3.500 0.7821 0.00873 0.00274 -0.0971 0.4572 0.7595
3.750 0.8067 0.00892 0.00291 -0.0965 0.4357 0.7721
4.000 0.8315 0.00910 0.00308 -0.0959 0.4147 0.7860
4.250 0.8554 0.00933 0.00328 -0.0952 0.3910 0.8016
4.500 0.8779 0.00963 0.00351 -0.0942 0.3556 0.8195
4.750 0.8978 0.01011 0.00381 -0.0927 0.3039 0.8399
5.000 0.9148 0.01078 0.00421 -0.0908 0.2353 0.8645
5.250 0.9311 0.01130 0.00457 -0.0886 0.1864 0.9011
5.500 0.9534 0.01169 0.00487 -0.0877 0.1526 1.0000
5.750 0.9761 0.01218 0.00524 -0.0869 0.1255 1.0000
6.000 0.9974 0.01277 0.00567 -0.0860 0.0950 1.0000
6.250 1.0194 0.01329 0.00608 -0.0851 0.0734 1.0000
6.500 1.0408 0.01385 0.00653 -0.0841 0.0533 1.0000
6.750 1.0609 0.01449 0.00704 -0.0830 0.0327 1.0000
7.000 1.0800 0.01521 0.00765 -0.0816 0.0148 1.0000
7.250 1.1007 0.01578 0.00821 -0.0805 0.0105 1.0000
7.500 1.1217 0.01629 0.00875 -0.0794 0.0092 1.0000
7.750 1.1419 0.01686 0.00937 -0.0781 0.0083 1.0000
8.000 1.1624 0.01737 0.00995 -0.0770 0.0080 1.0000
8.250 1.1820 0.01793 0.01059 -0.0756 0.0076 1.0000
8.500 1.2006 0.01852 0.01125 -0.0742 0.0073 1.0000
8.750 1.2174 0.01914 0.01194 -0.0724 0.0070 1.0000
9.000 1.2330 0.01980 0.01267 -0.0705 0.0066 1.0000
9.250 1.2477 0.02052 0.01345 -0.0684 0.0063 1.0000
9.500 1.2608 0.02133 0.01433 -0.0662 0.0060 1.0000
9.750 1.2710 0.02233 0.01541 -0.0636 0.0058 1.0000
10.000 1.2787 0.02350 0.01669 -0.0607 0.0056 1.0000
10.250 1.2881 0.02455 0.01783 -0.0582 0.0055 1.0000
10.500 1.2981 0.02557 0.01894 -0.0559 0.0054 1.0000
10.750 1.3072 0.02668 0.02015 -0.0536 0.0054 1.0000
11.000 1.3158 0.02784 0.02141 -0.0514 0.0053 1.0000
11.250 1.3220 0.02922 0.02290 -0.0490 0.0052 1.0000
11.500 1.3286 0.03062 0.02440 -0.0469 0.0051 1.0000
11.750 1.3332 0.03223 0.02613 -0.0448 0.0051 1.0000
12.000 1.3381 0.03390 0.02793 -0.0430 0.0049 1.0000
12.250 1.3412 0.03581 0.02996 -0.0413 0.0049 1.0000
12.500 1.3438 0.03785 0.03212 -0.0397 0.0048 1.0000
12.750 1.3454 0.04009 0.03450 -0.0384 0.0048 1.0000
13.000 1.3464 0.04251 0.03705 -0.0374 0.0047 1.0000
13.250 1.3462 0.04517 0.03985 -0.0366 0.0046 1.0000
13.500 1.3453 0.04804 0.04286 -0.0361 0.0046 1.0000
13.750 1.3433 0.05116 0.04613 -0.0358 0.0045 1.0000
14.000 1.3403 0.05455 0.04967 -0.0359 0.0045 1.0000
14.250 1.3359 0.05827 0.05355 -0.0363 0.0044 1.0000
14.500 1.3307 0.06228 0.05771 -0.0370 0.0044 1.0000
14.750 1.3243 0.06664 0.06223 -0.0381 0.0044 1.0000
15.000 1.3165 0.07141 0.06716 -0.0396 0.0044 1.0000
15.250 1.3081 0.07651 0.07241 -0.0415 0.0043 1.0000
15.500 1.2981 0.08207 0.07814 -0.0437 0.0043 1.0000
15.750 1.2871 0.08807 0.08431 -0.0465 0.0043 1.0000
16.000 1.2751 0.09453 0.09093 -0.0496 0.0043 1.0000
16.250 1.2622 0.10147 0.09804 -0.0532 0.0043 1.0000
16.500 1.2483 0.10887 0.10560 -0.0573 0.0043 1.0000
16.750 1.2336 0.11675 0.11365 -0.0618 0.0043 1.0000
17.000 1.2181 0.12516 0.12223 -0.0668 0.0043 1.0000
17.250 1.2023 0.13392 0.13114 -0.0721 0.0043 1.0000
17.500 1.1855 0.14329 0.14067 -0.0779 0.0043 1.0000
17.750 1.1679 0.15329 0.15083 -0.0842 0.0044 1.0000
18.000 1.1476 0.16453 0.16222 -0.0912 0.0044 1.0000
18.250 1.1215 0.17830 0.17616 -0.0997 0.0045 1.0000
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Polar data table (+)
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