E201 (11.88%) (e201-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E201 (11.88%) (e201-il) Reynolds number: 200,000 Max Cl/Cd: 78.16 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e201-il-200000-n5.txt Download as CSV file: xf-e201-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E201 (11.88%)
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4145 0.09007 0.08646 -0.0439 1.0000 0.0172
-10.000 -0.4238 0.08442 0.08087 -0.0462 1.0000 0.0171
-9.500 -0.5619 0.05040 0.04671 -0.0669 1.0000 0.0151
-9.250 -0.5887 0.04692 0.04308 -0.0650 1.0000 0.0151
-9.000 -0.5983 0.04250 0.03832 -0.0656 0.9966 0.0150
-8.750 -0.5825 0.03776 0.03314 -0.0698 0.9874 0.0152
-8.500 -0.5609 0.03456 0.02960 -0.0725 0.9793 0.0155
-8.250 -0.5335 0.03265 0.02749 -0.0748 0.9723 0.0164
-8.000 -0.5110 0.03007 0.02455 -0.0760 0.9621 0.0168
-7.750 -0.4863 0.02746 0.02152 -0.0772 0.9525 0.0171
-7.500 -0.4589 0.02514 0.01880 -0.0783 0.9434 0.0173
-7.250 -0.4323 0.02331 0.01666 -0.0788 0.9320 0.0175
-7.000 -0.4033 0.02171 0.01481 -0.0796 0.9212 0.0178
-6.750 -0.3728 0.02033 0.01321 -0.0805 0.9105 0.0182
-6.500 -0.3418 0.01911 0.01178 -0.0815 0.8992 0.0187
-6.250 -0.3119 0.01809 0.01059 -0.0821 0.8863 0.0192
-6.000 -0.2832 0.01721 0.00957 -0.0825 0.8725 0.0197
-5.750 -0.2564 0.01629 0.00855 -0.0826 0.8582 0.0208
-5.500 -0.2293 0.01572 0.00788 -0.0827 0.8441 0.0226
-5.250 -0.2029 0.01519 0.00719 -0.0825 0.8303 0.0242
-5.000 -0.1768 0.01470 0.00654 -0.0821 0.8171 0.0254
-4.750 -0.1511 0.01419 0.00592 -0.0818 0.8046 0.0278
-4.500 -0.1250 0.01379 0.00540 -0.0814 0.7930 0.0325
-4.250 -0.0994 0.01332 0.00491 -0.0810 0.7821 0.0471
-4.000 -0.0741 0.01287 0.00454 -0.0807 0.7712 0.0797
-3.750 -0.0488 0.01244 0.00425 -0.0805 0.7613 0.1237
-3.250 0.0021 0.01168 0.00377 -0.0800 0.7428 0.2325
-3.000 0.0272 0.01130 0.00361 -0.0797 0.7346 0.3048
-2.750 0.0525 0.01102 0.00352 -0.0793 0.7261 0.3764
-2.500 0.0786 0.01087 0.00344 -0.0790 0.7185 0.4285
-2.250 0.1048 0.01076 0.00337 -0.0786 0.7108 0.4703
-2.000 0.1314 0.01068 0.00330 -0.0783 0.7038 0.5026
-1.750 0.1580 0.01061 0.00324 -0.0780 0.6966 0.5315
-1.500 0.1845 0.01055 0.00319 -0.0777 0.6902 0.5596
-1.250 0.2110 0.01049 0.00316 -0.0773 0.6832 0.5872
-1.000 0.2375 0.01045 0.00312 -0.0769 0.6774 0.6154
-0.750 0.2638 0.01039 0.00312 -0.0765 0.6706 0.6449
-0.500 0.2898 0.01034 0.00312 -0.0760 0.6647 0.6766
-0.250 0.3156 0.01028 0.00314 -0.0755 0.6588 0.7103
0.000 0.3411 0.01023 0.00317 -0.0748 0.6527 0.7471
0.250 0.3662 0.01019 0.00320 -0.0739 0.6476 0.7883
0.500 0.3918 0.01013 0.00326 -0.0731 0.6413 0.8354
0.750 0.4218 0.01012 0.00330 -0.0732 0.6358 0.8853
1.000 0.4594 0.01014 0.00333 -0.0751 0.6302 0.9306
1.250 0.4990 0.01018 0.00336 -0.0776 0.6241 0.9670
1.500 0.5385 0.01026 0.00335 -0.0801 0.6189 0.9936
1.750 0.5674 0.01035 0.00344 -0.0805 0.6128 1.0000
2.000 0.5923 0.01046 0.00352 -0.0800 0.6073 1.0000
2.250 0.6176 0.01059 0.00360 -0.0796 0.6021 1.0000
2.500 0.6428 0.01071 0.00372 -0.0791 0.5960 1.0000
2.750 0.6685 0.01084 0.00382 -0.0787 0.5907 1.0000
3.000 0.6941 0.01097 0.00397 -0.0783 0.5846 1.0000
3.250 0.7197 0.01110 0.00410 -0.0779 0.5780 1.0000
3.500 0.7453 0.01123 0.00423 -0.0775 0.5713 1.0000
3.750 0.7707 0.01136 0.00438 -0.0771 0.5634 1.0000
4.000 0.7962 0.01149 0.00454 -0.0766 0.5556 1.0000
4.250 0.8215 0.01163 0.00468 -0.0762 0.5470 1.0000
4.500 0.8466 0.01176 0.00486 -0.0757 0.5373 1.0000
4.750 0.8716 0.01190 0.00503 -0.0751 0.5274 1.0000
5.000 0.8964 0.01205 0.00520 -0.0745 0.5171 1.0000
5.250 0.9210 0.01220 0.00540 -0.0739 0.5054 1.0000
5.500 0.9453 0.01237 0.00560 -0.0733 0.4926 1.0000
5.750 0.9692 0.01255 0.00583 -0.0726 0.4782 1.0000
6.000 0.9926 0.01275 0.00606 -0.0717 0.4622 1.0000
6.250 1.0153 0.01299 0.00630 -0.0708 0.4441 1.0000
6.500 1.0372 0.01327 0.00658 -0.0698 0.4204 1.0000
6.750 1.0569 0.01365 0.00690 -0.0684 0.3888 1.0000
7.000 1.0726 0.01425 0.00729 -0.0664 0.3413 1.0000
7.250 1.0836 0.01516 0.00789 -0.0638 0.2814 1.0000
7.500 1.0923 0.01627 0.00866 -0.0611 0.2241 1.0000
7.750 1.1016 0.01735 0.00948 -0.0585 0.1773 1.0000
8.000 1.1120 0.01835 0.01028 -0.0561 0.1423 1.0000
8.250 1.1223 0.01930 0.01111 -0.0537 0.1138 1.0000
8.500 1.1300 0.02025 0.01194 -0.0508 0.0898 1.0000
8.750 1.1367 0.02126 0.01284 -0.0480 0.0686 1.0000
9.000 1.1443 0.02229 0.01380 -0.0453 0.0517 1.0000
9.250 1.1497 0.02349 0.01491 -0.0427 0.0363 1.0000
9.500 1.1550 0.02476 0.01615 -0.0401 0.0251 1.0000
9.750 1.1614 0.02603 0.01744 -0.0379 0.0202 1.0000
10.000 1.1678 0.02738 0.01885 -0.0359 0.0170 1.0000
10.250 1.1738 0.02883 0.02038 -0.0340 0.0156 1.0000
10.500 1.1806 0.03029 0.02195 -0.0324 0.0146 1.0000
10.750 1.1869 0.03185 0.02363 -0.0310 0.0138 1.0000
11.000 1.1918 0.03361 0.02550 -0.0296 0.0131 1.0000
11.250 1.1962 0.03547 0.02746 -0.0284 0.0126 1.0000
11.500 1.1983 0.03763 0.02972 -0.0273 0.0121 1.0000
11.750 1.2005 0.03984 0.03204 -0.0264 0.0116 1.0000
12.000 1.2039 0.04203 0.03436 -0.0256 0.0112 1.0000
12.250 1.2069 0.04431 0.03676 -0.0250 0.0109 1.0000
12.500 1.2097 0.04666 0.03926 -0.0244 0.0103 1.0000
12.750 1.2117 0.04918 0.04188 -0.0240 0.0101 1.0000
13.000 1.2126 0.05186 0.04468 -0.0237 0.0099 1.0000
13.250 1.2135 0.05462 0.04756 -0.0235 0.0097 1.0000
13.500 1.2139 0.05750 0.05056 -0.0234 0.0095 1.0000
13.750 1.2140 0.06051 0.05368 -0.0235 0.0093 1.0000
14.000 1.2143 0.06357 0.05684 -0.0236 0.0092 1.0000
14.250 1.2140 0.06680 0.06019 -0.0239 0.0091 1.0000
14.500 1.2132 0.07015 0.06365 -0.0242 0.0090 1.0000
14.750 1.2127 0.07356 0.06719 -0.0247 0.0089 1.0000
15.000 1.2114 0.07718 0.07093 -0.0253 0.0088 1.0000
15.250 1.2097 0.08095 0.07483 -0.0259 0.0087 1.0000
15.500 1.2064 0.08508 0.07912 -0.0269 0.0085 1.0000
15.750 1.2035 0.08928 0.08351 -0.0281 0.0085 1.0000
16.000 1.1993 0.09380 0.08821 -0.0296 0.0085 1.0000
16.250 1.1945 0.09853 0.09311 -0.0314 0.0085 1.0000
16.500 1.1867 0.10398 0.09877 -0.0337 0.0084 1.0000
16.750 1.1792 0.10948 0.10445 -0.0362 0.0084 1.0000
17.000 1.1704 0.11544 0.11060 -0.0392 0.0084 1.0000
17.250 1.1602 0.12187 0.11722 -0.0426 0.0084 1.0000
17.500 1.1483 0.12892 0.12446 -0.0466 0.0084 1.0000
17.750 1.1366 0.13616 0.13188 -0.0509 0.0084 1.0000
18.000 1.1237 0.14400 0.13990 -0.0557 0.0084 1.0000
18.250 1.1106 0.15225 0.14831 -0.0609 0.0085 1.0000
18.500 1.0956 0.16142 0.15764 -0.0668 0.0085 1.0000
18.750 1.0805 0.17100 0.16736 -0.0729 0.0086 1.0000
19.000 1.0583 0.18404 0.18057 -0.0811 0.0087 1.0000
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Polar data table (+)
Polar graphs
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