E203 (13.64%) (e203-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E203 (13.64%) (e203-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.55 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e203-il-1000000-n5.txt Download as CSV file: xf-e203-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E203 (13.64%)
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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.5262 0.18798 0.18614 -0.0083 1.0000 0.0043
-17.250 -0.7326 0.12117 0.11910 -0.0342 1.0000 0.0067
-17.000 -0.7829 0.10679 0.10454 -0.0414 1.0000 0.0067
-16.750 -0.8166 0.09636 0.09399 -0.0469 1.0000 0.0067
-16.500 -0.8504 0.08634 0.08383 -0.0523 1.0000 0.0066
-16.250 -0.8751 0.07820 0.07557 -0.0568 1.0000 0.0066
-16.000 -0.8955 0.07105 0.06830 -0.0608 1.0000 0.0066
-15.750 -0.9073 0.06560 0.06275 -0.0639 1.0000 0.0067
-15.500 -0.9258 0.05952 0.05655 -0.0672 1.0000 0.0067
-15.250 -0.9415 0.05413 0.05105 -0.0701 1.0000 0.0067
-15.000 -0.9486 0.05007 0.04690 -0.0722 1.0000 0.0068
-14.750 -0.9575 0.04594 0.04267 -0.0742 1.0000 0.0068
-14.500 -0.9665 0.04197 0.03859 -0.0760 1.0000 0.0069
-14.250 -0.9686 0.03894 0.03548 -0.0773 1.0000 0.0070
-14.000 -0.9711 0.03603 0.03246 -0.0783 1.0000 0.0070
-13.750 -0.9745 0.03323 0.02957 -0.0790 1.0000 0.0071
-13.500 -0.9763 0.03091 0.02715 -0.0791 1.0000 0.0072
-13.250 -0.9751 0.02919 0.02537 -0.0786 1.0000 0.0074
-13.000 -0.9783 0.02761 0.02372 -0.0772 1.0000 0.0075
-12.750 -0.9786 0.02587 0.02187 -0.0765 0.9988 0.0075
-12.500 -0.9592 0.02464 0.02054 -0.0777 0.9958 0.0077
-12.250 -0.9367 0.02346 0.01926 -0.0789 0.9930 0.0078
-12.000 -0.9159 0.02233 0.01802 -0.0796 0.9898 0.0079
-11.750 -0.8903 0.02149 0.01710 -0.0806 0.9871 0.0081
-11.500 -0.8634 0.02055 0.01606 -0.0820 0.9848 0.0082
-11.250 -0.8341 0.01975 0.01518 -0.0835 0.9832 0.0083
-11.000 -0.8146 0.01881 0.01415 -0.0832 0.9780 0.0084
-10.750 -0.7907 0.01761 0.01285 -0.0840 0.9735 0.0088
-10.250 -0.7402 0.01618 0.01131 -0.0847 0.9619 0.0092
-10.000 -0.7115 0.01555 0.01062 -0.0857 0.9551 0.0094
-9.750 -0.6837 0.01498 0.00997 -0.0863 0.9434 0.0097
-9.500 -0.6543 0.01440 0.00932 -0.0871 0.9267 0.0099
-9.250 -0.6275 0.01392 0.00870 -0.0873 0.9022 0.0102
-9.000 -0.6042 0.01353 0.00816 -0.0868 0.8750 0.0105
-8.750 -0.5817 0.01318 0.00766 -0.0860 0.8515 0.0107
-8.500 -0.5585 0.01288 0.00723 -0.0853 0.8303 0.0110
-8.250 -0.5350 0.01261 0.00684 -0.0847 0.8113 0.0113
-8.000 -0.5107 0.01237 0.00649 -0.0842 0.7943 0.0115
-7.750 -0.4863 0.01209 0.00611 -0.0838 0.7791 0.0116
-7.500 -0.4619 0.01178 0.00571 -0.0833 0.7653 0.0119
-7.250 -0.4377 0.01139 0.00520 -0.0828 0.7521 0.0123
-7.000 -0.4126 0.01107 0.00480 -0.0825 0.7400 0.0127
-6.750 -0.3870 0.01081 0.00447 -0.0822 0.7291 0.0132
-6.500 -0.3611 0.01058 0.00417 -0.0820 0.7189 0.0137
-6.250 -0.3349 0.01037 0.00390 -0.0818 0.7088 0.0142
-6.000 -0.3084 0.01018 0.00364 -0.0816 0.6996 0.0149
-5.750 -0.2818 0.01001 0.00341 -0.0814 0.6911 0.0154
-5.500 -0.2548 0.00984 0.00319 -0.0814 0.6828 0.0164
-5.250 -0.2281 0.00965 0.00297 -0.0812 0.6751 0.0188
-5.000 -0.2011 0.00946 0.00275 -0.0811 0.6677 0.0231
-4.750 -0.1749 0.00916 0.00252 -0.0810 0.6609 0.0420
-4.500 -0.1479 0.00895 0.00234 -0.0810 0.6539 0.0573
-4.000 -0.0940 0.00850 0.00200 -0.0809 0.6415 0.1005
-3.750 -0.0669 0.00832 0.00187 -0.0809 0.6351 0.1233
-3.500 -0.0399 0.00809 0.00173 -0.0809 0.6296 0.1546
-3.250 -0.0130 0.00780 0.00159 -0.0809 0.6240 0.1992
-3.000 0.0140 0.00759 0.00147 -0.0809 0.6185 0.2368
-2.750 0.0416 0.00741 0.00138 -0.0809 0.6134 0.2687
-2.500 0.0686 0.00716 0.00129 -0.0810 0.6080 0.3193
-2.000 0.1238 0.00689 0.00122 -0.0810 0.5982 0.3999
-1.750 0.1520 0.00687 0.00120 -0.0811 0.5929 0.4119
-1.250 0.2086 0.00685 0.00117 -0.0813 0.5835 0.4327
-1.000 0.2369 0.00684 0.00116 -0.0814 0.5784 0.4421
-0.500 0.2934 0.00685 0.00116 -0.0815 0.5692 0.4585
-0.250 0.3217 0.00685 0.00117 -0.0816 0.5642 0.4662
0.000 0.3498 0.00688 0.00118 -0.0817 0.5593 0.4736
0.250 0.3781 0.00688 0.00120 -0.0818 0.5549 0.4805
0.500 0.4064 0.00689 0.00122 -0.0819 0.5498 0.4882
0.750 0.4343 0.00691 0.00124 -0.0819 0.5449 0.4966
1.000 0.4626 0.00693 0.00127 -0.0820 0.5403 0.5053
1.250 0.4907 0.00694 0.00131 -0.0820 0.5350 0.5126
1.500 0.5185 0.00699 0.00135 -0.0821 0.5297 0.5201
1.750 0.5467 0.00700 0.00139 -0.0821 0.5239 0.5272
2.000 0.5743 0.00706 0.00145 -0.0821 0.5162 0.5353
2.250 0.6021 0.00709 0.00150 -0.0821 0.5082 0.5434
2.750 0.6572 0.00720 0.00163 -0.0821 0.4922 0.5616
3.000 0.6844 0.00726 0.00171 -0.0820 0.4833 0.5721
3.250 0.7117 0.00733 0.00179 -0.0819 0.4732 0.5832
3.500 0.7388 0.00740 0.00188 -0.0818 0.4625 0.5952
3.750 0.7656 0.00749 0.00199 -0.0817 0.4514 0.6085
4.000 0.7921 0.00759 0.00210 -0.0815 0.4386 0.6237
4.250 0.8184 0.00770 0.00222 -0.0812 0.4249 0.6405
4.500 0.8443 0.00784 0.00237 -0.0809 0.4081 0.6584
4.750 0.8695 0.00801 0.00253 -0.0805 0.3878 0.6775
5.000 0.8937 0.00824 0.00273 -0.0800 0.3617 0.6990
5.250 0.9165 0.00855 0.00297 -0.0792 0.3288 0.7249
5.500 0.9361 0.00906 0.00334 -0.0779 0.2795 0.7545
5.750 0.9533 0.00971 0.00379 -0.0761 0.2226 0.7876
6.000 0.9731 0.01009 0.00413 -0.0748 0.1909 0.8255
6.250 0.9917 0.01040 0.00446 -0.0731 0.1657 0.8742
6.500 1.0106 0.01080 0.00486 -0.0715 0.1314 0.9644
6.750 1.0340 0.01138 0.00529 -0.0711 0.1018 1.0000
7.000 1.0543 0.01184 0.00565 -0.0700 0.0827 1.0000
7.250 1.0740 0.01232 0.00603 -0.0687 0.0661 1.0000
7.750 1.1123 0.01326 0.00683 -0.0660 0.0410 1.0000
8.000 1.1307 0.01374 0.00726 -0.0646 0.0313 1.0000
8.250 1.1484 0.01421 0.00770 -0.0630 0.0243 1.0000
8.500 1.1633 0.01469 0.00815 -0.0609 0.0176 1.0000
8.750 1.1752 0.01528 0.00869 -0.0583 0.0105 1.0000
9.000 1.1887 0.01581 0.00922 -0.0560 0.0075 1.0000
9.250 1.2040 0.01629 0.00972 -0.0541 0.0066 1.0000
9.500 1.2181 0.01682 0.01029 -0.0520 0.0058 1.0000
9.750 1.2319 0.01739 0.01088 -0.0500 0.0054 1.0000
10.000 1.2456 0.01797 0.01151 -0.0481 0.0051 1.0000
10.250 1.2594 0.01857 0.01215 -0.0462 0.0049 1.0000
10.500 1.2725 0.01922 0.01284 -0.0444 0.0047 1.0000
10.750 1.2847 0.01995 0.01362 -0.0425 0.0045 1.0000
11.000 1.2967 0.02072 0.01444 -0.0408 0.0044 1.0000
11.250 1.3076 0.02159 0.01536 -0.0390 0.0043 1.0000
11.500 1.3177 0.02255 0.01638 -0.0372 0.0042 1.0000
11.750 1.3275 0.02358 0.01746 -0.0356 0.0040 1.0000
12.000 1.3372 0.02467 0.01860 -0.0341 0.0039 1.0000
12.250 1.3457 0.02589 0.01989 -0.0326 0.0039 1.0000
12.500 1.3523 0.02732 0.02138 -0.0311 0.0037 1.0000
12.750 1.3588 0.02883 0.02295 -0.0298 0.0035 1.0000
13.000 1.3640 0.03050 0.02470 -0.0286 0.0035 1.0000
13.250 1.3649 0.03262 0.02691 -0.0273 0.0033 1.0000
13.500 1.3714 0.03432 0.02869 -0.0264 0.0033 1.0000
13.750 1.3758 0.03626 0.03071 -0.0256 0.0032 1.0000
14.000 1.3830 0.03798 0.03250 -0.0250 0.0032 1.0000
14.250 1.3898 0.03979 0.03437 -0.0245 0.0031 1.0000
14.500 1.3916 0.04216 0.03682 -0.0239 0.0031 1.0000
14.750 1.3960 0.04433 0.03907 -0.0236 0.0030 1.0000
15.000 1.3972 0.04690 0.04173 -0.0233 0.0030 1.0000
15.250 1.4013 0.04923 0.04413 -0.0232 0.0029 1.0000
15.500 1.4016 0.05206 0.04705 -0.0232 0.0029 1.0000
15.750 1.4012 0.05506 0.05014 -0.0234 0.0029 1.0000
16.000 1.4019 0.05803 0.05320 -0.0237 0.0028 1.0000
16.250 1.3999 0.06142 0.05669 -0.0242 0.0028 1.0000
16.500 1.4000 0.06463 0.06000 -0.0248 0.0027 1.0000
16.750 1.3976 0.06828 0.06375 -0.0256 0.0027 1.0000
17.000 1.3925 0.07244 0.06801 -0.0267 0.0026 1.0000
17.250 1.3896 0.07636 0.07203 -0.0278 0.0027 1.0000
17.500 1.3846 0.08071 0.07648 -0.0292 0.0026 1.0000
17.750 1.3791 0.08526 0.08114 -0.0308 0.0026 1.0000
18.000 1.3720 0.09022 0.08621 -0.0327 0.0026 1.0000
18.250 1.3652 0.09521 0.09131 -0.0347 0.0026 1.0000
18.500 1.3557 0.10081 0.09702 -0.0371 0.0025 1.0000
18.750 1.3479 0.10623 0.10255 -0.0396 0.0025 1.0000
19.000 1.3368 0.11238 0.10883 -0.0426 0.0025 1.0000
19.250 1.3270 0.11841 0.11497 -0.0456 0.0025 1.0000
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