E203 (13.64%) (e203-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E203 (13.64%) (e203-il) Reynolds number: 200,000 Max Cl/Cd: 75.87 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e203-il-200000-n5.txt Download as CSV file: xf-e203-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6358 0.06965 0.06543 -0.0656 1.0000 0.0161
-12.500 -0.6580 0.06303 0.05865 -0.0700 1.0000 0.0161
-12.250 -0.6757 0.05770 0.05316 -0.0733 1.0000 0.0160
-12.000 -0.6915 0.05317 0.04846 -0.0757 1.0000 0.0159
-11.750 -0.7089 0.04891 0.04405 -0.0772 1.0000 0.0160
-11.500 -0.7231 0.04565 0.04063 -0.0776 1.0000 0.0160
-11.250 -0.7388 0.04287 0.03772 -0.0765 1.0000 0.0161
-11.000 -0.7559 0.04086 0.03559 -0.0736 1.0000 0.0162
-10.750 -0.7687 0.03905 0.03366 -0.0700 1.0000 0.0163
-10.500 -0.7743 0.03721 0.03169 -0.0671 1.0000 0.0164
-10.250 -0.7765 0.03549 0.02985 -0.0643 1.0000 0.0166
-10.000 -0.7741 0.03391 0.02813 -0.0619 0.9997 0.0168
-9.750 -0.7472 0.03190 0.02592 -0.0644 0.9949 0.0174
-9.500 -0.7203 0.03021 0.02403 -0.0663 0.9895 0.0181
-9.250 -0.6911 0.02858 0.02219 -0.0683 0.9845 0.0189
-9.000 -0.6641 0.02697 0.02036 -0.0696 0.9784 0.0196
-8.750 -0.6352 0.02541 0.01861 -0.0710 0.9726 0.0201
-8.500 -0.6078 0.02406 0.01710 -0.0719 0.9656 0.0206
-8.250 -0.5787 0.02285 0.01572 -0.0730 0.9587 0.0210
-8.000 -0.5539 0.02147 0.01427 -0.0734 0.9496 0.0217
-7.750 -0.5239 0.02031 0.01304 -0.0748 0.9427 0.0225
-7.500 -0.4975 0.01945 0.01212 -0.0752 0.9319 0.0237
-7.250 -0.4680 0.01866 0.01124 -0.0761 0.9224 0.0253
-7.000 -0.4355 0.01786 0.01029 -0.0775 0.9140 0.0269
-6.750 -0.4062 0.01701 0.00935 -0.0783 0.9028 0.0286
-6.500 -0.3754 0.01627 0.00852 -0.0794 0.8917 0.0313
-6.250 -0.3436 0.01565 0.00778 -0.0804 0.8803 0.0353
-6.000 -0.3130 0.01498 0.00706 -0.0813 0.8680 0.0457
-5.500 -0.2566 0.01377 0.00596 -0.0822 0.8415 0.0967
-5.250 -0.2298 0.01329 0.00553 -0.0823 0.8282 0.1273
-5.000 -0.2036 0.01283 0.00514 -0.0823 0.8154 0.1653
-4.750 -0.1782 0.01235 0.00479 -0.0822 0.8032 0.2147
-4.500 -0.1533 0.01185 0.00450 -0.0821 0.7917 0.2792
-4.000 -0.1015 0.01140 0.00423 -0.0815 0.7702 0.3785
-3.750 -0.0745 0.01135 0.00413 -0.0813 0.7603 0.4092
-3.250 -0.0202 0.01130 0.00395 -0.0809 0.7419 0.4502
-3.000 0.0071 0.01130 0.00385 -0.0808 0.7337 0.4649
-2.750 0.0344 0.01129 0.00376 -0.0806 0.7252 0.4784
-2.250 0.0891 0.01127 0.00362 -0.0803 0.7099 0.5024
-2.000 0.1164 0.01127 0.00357 -0.0802 0.7028 0.5132
-1.750 0.1438 0.01127 0.00352 -0.0800 0.6956 0.5240
-1.500 0.1713 0.01127 0.00347 -0.0799 0.6891 0.5343
-1.250 0.1985 0.01126 0.00345 -0.0798 0.6821 0.5436
-1.000 0.2261 0.01128 0.00341 -0.0797 0.6763 0.5535
-0.750 0.2533 0.01128 0.00341 -0.0796 0.6695 0.5635
-0.500 0.2807 0.01129 0.00340 -0.0795 0.6637 0.5733
-0.250 0.3081 0.01130 0.00341 -0.0794 0.6576 0.5832
0.000 0.3354 0.01131 0.00343 -0.0793 0.6516 0.5929
0.250 0.3628 0.01133 0.00344 -0.0791 0.6463 0.6026
0.500 0.3900 0.01135 0.00349 -0.0790 0.6400 0.6133
0.750 0.4173 0.01137 0.00353 -0.0789 0.6347 0.6244
1.000 0.4444 0.01140 0.00359 -0.0787 0.6292 0.6360
1.250 0.4712 0.01142 0.00367 -0.0785 0.6233 0.6492
1.500 0.4983 0.01146 0.00374 -0.0784 0.6184 0.6636
1.750 0.5249 0.01148 0.00385 -0.0781 0.6126 0.6791
2.000 0.5514 0.01151 0.00396 -0.0778 0.6069 0.6969
2.250 0.5780 0.01155 0.00405 -0.0775 0.6022 0.7173
2.500 0.6035 0.01157 0.00420 -0.0770 0.5960 0.7393
2.750 0.6292 0.01160 0.00432 -0.0764 0.5906 0.7644
3.000 0.6544 0.01162 0.00447 -0.0758 0.5851 0.7938
3.250 0.6787 0.01163 0.00463 -0.0749 0.5788 0.8283
3.750 0.7337 0.01166 0.00489 -0.0743 0.5648 0.9171
4.000 0.7725 0.01172 0.00498 -0.0766 0.5567 0.9752
4.250 0.8015 0.01183 0.00512 -0.0770 0.5478 1.0000
4.500 0.8268 0.01197 0.00527 -0.0766 0.5394 1.0000
4.750 0.8518 0.01211 0.00542 -0.0761 0.5302 1.0000
5.000 0.8764 0.01225 0.00560 -0.0756 0.5195 1.0000
5.250 0.9010 0.01240 0.00577 -0.0750 0.5088 1.0000
5.500 0.9252 0.01257 0.00595 -0.0743 0.4973 1.0000
5.750 0.9490 0.01275 0.00616 -0.0736 0.4845 1.0000
6.000 0.9722 0.01294 0.00637 -0.0728 0.4696 1.0000
6.250 0.9949 0.01315 0.00660 -0.0719 0.4524 1.0000
6.500 1.0167 0.01340 0.00685 -0.0708 0.4320 1.0000
6.750 1.0372 0.01372 0.00714 -0.0695 0.4080 1.0000
7.000 1.0559 0.01411 0.00747 -0.0680 0.3785 1.0000
7.250 1.0718 0.01465 0.00786 -0.0660 0.3417 1.0000
7.500 1.0844 0.01536 0.00838 -0.0636 0.2991 1.0000
7.750 1.0956 0.01617 0.00901 -0.0611 0.2599 1.0000
8.000 1.1056 0.01704 0.00971 -0.0585 0.2256 1.0000
8.250 1.1136 0.01795 0.01048 -0.0555 0.1917 1.0000
8.500 1.1192 0.01891 0.01128 -0.0522 0.1611 1.0000
8.750 1.1237 0.01997 0.01217 -0.0490 0.1316 1.0000
9.000 1.1286 0.02108 0.01313 -0.0461 0.1061 1.0000
9.250 1.1339 0.02223 0.01415 -0.0433 0.0852 1.0000
9.500 1.1411 0.02332 0.01519 -0.0410 0.0703 1.0000
9.750 1.1490 0.02442 0.01627 -0.0389 0.0600 1.0000
10.000 1.1562 0.02562 0.01749 -0.0369 0.0509 1.0000
10.250 1.1627 0.02693 0.01880 -0.0350 0.0420 1.0000
10.500 1.1688 0.02834 0.02022 -0.0333 0.0339 1.0000
10.750 1.1735 0.02994 0.02182 -0.0316 0.0266 1.0000
11.000 1.1784 0.03160 0.02352 -0.0301 0.0221 1.0000
11.250 1.1816 0.03349 0.02543 -0.0287 0.0188 1.0000
11.500 1.1867 0.03530 0.02733 -0.0275 0.0168 1.0000
11.750 1.1907 0.03726 0.02938 -0.0264 0.0153 1.0000
12.000 1.1935 0.03940 0.03160 -0.0255 0.0145 1.0000
12.250 1.1961 0.04164 0.03395 -0.0247 0.0138 1.0000
12.500 1.1984 0.04398 0.03643 -0.0240 0.0131 1.0000
12.750 1.2004 0.04640 0.03897 -0.0235 0.0126 1.0000
13.000 1.2019 0.04894 0.04163 -0.0231 0.0121 1.0000
13.250 1.2029 0.05160 0.04440 -0.0228 0.0117 1.0000
13.500 1.2037 0.05437 0.04728 -0.0227 0.0114 1.0000
13.750 1.2024 0.05746 0.05046 -0.0228 0.0109 1.0000
14.000 1.2001 0.06076 0.05386 -0.0230 0.0107 1.0000
14.250 1.1991 0.06401 0.05722 -0.0233 0.0104 1.0000
14.500 1.2004 0.06708 0.06043 -0.0237 0.0101 1.0000
14.750 1.1999 0.07046 0.06395 -0.0242 0.0097 1.0000
15.000 1.1990 0.07395 0.06757 -0.0248 0.0096 1.0000
15.250 1.1983 0.07754 0.07130 -0.0257 0.0093 1.0000
15.500 1.1963 0.08140 0.07529 -0.0266 0.0091 1.0000
15.750 1.1945 0.08529 0.07934 -0.0277 0.0090 1.0000
16.000 1.1918 0.08944 0.08363 -0.0290 0.0088 1.0000
16.250 1.1884 0.09379 0.08812 -0.0305 0.0087 1.0000
16.500 1.1851 0.09824 0.09270 -0.0322 0.0086 1.0000
16.750 1.1811 0.10289 0.09749 -0.0340 0.0085 1.0000
17.000 1.1760 0.10782 0.10256 -0.0362 0.0084 1.0000
17.250 1.1711 0.11283 0.10773 -0.0384 0.0083 1.0000
17.500 1.1652 0.11817 0.11321 -0.0410 0.0082 1.0000
17.750 1.1587 0.12373 0.11891 -0.0439 0.0082 1.0000
18.000 1.1516 0.12953 0.12488 -0.0470 0.0081 1.0000
18.250 1.1435 0.13573 0.13124 -0.0504 0.0081 1.0000
18.500 1.1346 0.14224 0.13789 -0.0543 0.0081 1.0000
18.750 1.1245 0.14929 0.14512 -0.0586 0.0081 1.0000
19.000 1.1124 0.15706 0.15306 -0.0634 0.0081 1.0000
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Polar data table (+)
Polar graphs
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