E201 (11.88%) (e201-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E201 (11.88%) (e201-il) Reynolds number: 500,000 Max Cl/Cd: 104.63 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e201-il-500000-n5.txt Download as CSV file: xf-e201-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5887 0.05438 0.05195 -0.0627 1.0000 0.0091
-10.500 -0.6296 0.04444 0.04181 -0.0714 1.0000 0.0089
-10.250 -0.6597 0.04138 0.03865 -0.0699 1.0000 0.0088
-10.000 -0.6570 0.03562 0.03247 -0.0755 0.9910 0.0090
-9.750 -0.6430 0.03146 0.02789 -0.0789 0.9845 0.0092
-9.500 -0.6274 0.02842 0.02449 -0.0802 0.9761 0.0092
-9.250 -0.6047 0.02598 0.02173 -0.0817 0.9695 0.0095
-8.750 -0.5585 0.02230 0.01750 -0.0830 0.9488 0.0098
-8.500 -0.5310 0.02079 0.01574 -0.0840 0.9364 0.0099
-8.250 -0.5016 0.01956 0.01429 -0.0851 0.9215 0.0102
-8.000 -0.4734 0.01845 0.01296 -0.0858 0.9025 0.0103
-7.750 -0.4476 0.01767 0.01196 -0.0858 0.8816 0.0105
-7.500 -0.4241 0.01687 0.01095 -0.0853 0.8608 0.0107
-7.000 -0.3805 0.01499 0.00872 -0.0837 0.8234 0.0114
-6.750 -0.3572 0.01438 0.00798 -0.0831 0.8070 0.0116
-6.500 -0.3334 0.01383 0.00729 -0.0825 0.7922 0.0119
-6.250 -0.3092 0.01334 0.00668 -0.0819 0.7784 0.0122
-6.000 -0.2846 0.01290 0.00612 -0.0814 0.7658 0.0125
-5.750 -0.2596 0.01249 0.00561 -0.0810 0.7539 0.0129
-5.500 -0.2341 0.01212 0.00513 -0.0806 0.7429 0.0134
-5.250 -0.2084 0.01180 0.00469 -0.0803 0.7327 0.0138
-5.000 -0.1824 0.01152 0.00431 -0.0800 0.7231 0.0142
-4.750 -0.1559 0.01126 0.00396 -0.0797 0.7140 0.0146
-4.500 -0.1298 0.01096 0.00356 -0.0794 0.7056 0.0158
-4.250 -0.1032 0.01071 0.00326 -0.0792 0.6972 0.0175
-4.000 -0.0764 0.01052 0.00299 -0.0790 0.6898 0.0192
-3.750 -0.0496 0.01029 0.00274 -0.0789 0.6822 0.0250
-3.500 -0.0233 0.00998 0.00251 -0.0787 0.6753 0.0508
-3.250 0.0034 0.00972 0.00232 -0.0786 0.6684 0.0791
-3.000 0.0300 0.00949 0.00216 -0.0784 0.6621 0.1093
-2.750 0.0567 0.00922 0.00202 -0.0784 0.6555 0.1524
-2.500 0.0829 0.00891 0.00189 -0.0783 0.6494 0.2116
-2.250 0.1099 0.00870 0.00179 -0.0782 0.6437 0.2558
-2.000 0.1365 0.00845 0.00171 -0.0781 0.6376 0.3140
-1.750 0.1628 0.00820 0.00167 -0.0780 0.6322 0.3898
-1.500 0.1900 0.00807 0.00165 -0.0779 0.6266 0.4358
-1.250 0.2174 0.00801 0.00162 -0.0779 0.6211 0.4637
-1.000 0.2449 0.00797 0.00160 -0.0778 0.6160 0.4870
-0.750 0.2725 0.00792 0.00159 -0.0777 0.6105 0.5100
-0.500 0.2999 0.00789 0.00159 -0.0776 0.6054 0.5330
-0.250 0.3274 0.00785 0.00159 -0.0776 0.6005 0.5556
0.000 0.3549 0.00781 0.00160 -0.0775 0.5951 0.5800
0.250 0.3820 0.00778 0.00162 -0.0773 0.5902 0.6065
0.500 0.4093 0.00774 0.00166 -0.0772 0.5853 0.6344
0.750 0.4364 0.00769 0.00169 -0.0771 0.5801 0.6635
1.000 0.4631 0.00766 0.00174 -0.0768 0.5753 0.6966
1.250 0.4896 0.00760 0.00180 -0.0765 0.5704 0.7351
1.500 0.5155 0.00752 0.00187 -0.0760 0.5651 0.7786
1.750 0.5404 0.00747 0.00194 -0.0752 0.5603 0.8250
2.000 0.5651 0.00740 0.00202 -0.0743 0.5551 0.8743
2.250 0.5935 0.00739 0.00210 -0.0742 0.5494 0.9261
2.500 0.6310 0.00744 0.00216 -0.0763 0.5428 0.9641
2.750 0.6683 0.00751 0.00221 -0.0784 0.5346 0.9881
3.000 0.7009 0.00760 0.00229 -0.0795 0.5270 1.0000
3.250 0.7264 0.00770 0.00237 -0.0791 0.5188 1.0000
3.500 0.7521 0.00780 0.00245 -0.0787 0.5099 1.0000
3.750 0.7774 0.00793 0.00256 -0.0782 0.5003 1.0000
4.000 0.8032 0.00804 0.00267 -0.0779 0.4901 1.0000
4.250 0.8289 0.00817 0.00278 -0.0775 0.4799 1.0000
4.500 0.8544 0.00832 0.00291 -0.0770 0.4682 1.0000
4.750 0.8795 0.00849 0.00306 -0.0766 0.4541 1.0000
5.000 0.9045 0.00867 0.00322 -0.0761 0.4390 1.0000
5.250 0.9291 0.00888 0.00339 -0.0756 0.4217 1.0000
5.500 0.9520 0.00920 0.00360 -0.0747 0.3926 1.0000
5.750 0.9711 0.00978 0.00394 -0.0733 0.3396 1.0000
6.000 0.9868 0.01064 0.00443 -0.0715 0.2708 1.0000
6.250 1.0051 0.01134 0.00491 -0.0701 0.2249 1.0000
6.500 1.0230 0.01205 0.00540 -0.0687 0.1826 1.0000
6.750 1.0408 0.01275 0.00591 -0.0672 0.1459 1.0000
7.000 1.0582 0.01345 0.00644 -0.0657 0.1121 1.0000
7.250 1.0749 0.01417 0.00699 -0.0641 0.0826 1.0000
7.500 1.0928 0.01476 0.00750 -0.0626 0.0643 1.0000
7.750 1.1089 0.01545 0.00808 -0.0609 0.0452 1.0000
8.000 1.1248 0.01611 0.00867 -0.0592 0.0307 1.0000
8.250 1.1384 0.01686 0.00935 -0.0571 0.0171 1.0000
8.500 1.1501 0.01755 0.01002 -0.0545 0.0112 1.0000
8.750 1.1629 0.01818 0.01067 -0.0522 0.0095 1.0000
9.000 1.1757 0.01882 0.01136 -0.0500 0.0084 1.0000
9.250 1.1892 0.01945 0.01205 -0.0480 0.0079 1.0000
9.500 1.2017 0.02015 0.01282 -0.0459 0.0074 1.0000
9.750 1.2138 0.02089 0.01364 -0.0440 0.0071 1.0000
10.000 1.2243 0.02177 0.01458 -0.0419 0.0068 1.0000
10.250 1.2344 0.02270 0.01558 -0.0400 0.0066 1.0000
10.500 1.2428 0.02380 0.01676 -0.0380 0.0064 1.0000
10.750 1.2495 0.02507 0.01811 -0.0360 0.0061 1.0000
11.000 1.2532 0.02664 0.01977 -0.0340 0.0059 1.0000
11.250 1.2612 0.02797 0.02118 -0.0325 0.0058 1.0000
11.500 1.2676 0.02949 0.02279 -0.0311 0.0057 1.0000
11.750 1.2741 0.03108 0.02448 -0.0299 0.0056 1.0000
12.000 1.2786 0.03290 0.02640 -0.0287 0.0055 1.0000
12.250 1.2834 0.03476 0.02836 -0.0277 0.0055 1.0000
12.500 1.2872 0.03679 0.03049 -0.0268 0.0053 1.0000
12.750 1.2903 0.03896 0.03276 -0.0261 0.0052 1.0000
13.000 1.2926 0.04128 0.03517 -0.0254 0.0052 1.0000
13.250 1.2943 0.04370 0.03769 -0.0249 0.0051 1.0000
13.500 1.2955 0.04626 0.04035 -0.0245 0.0050 1.0000
13.750 1.2966 0.04890 0.04310 -0.0243 0.0049 1.0000
14.000 1.2970 0.05168 0.04598 -0.0241 0.0049 1.0000
14.250 1.2980 0.05451 0.04890 -0.0242 0.0048 1.0000
14.500 1.2979 0.05754 0.05205 -0.0243 0.0047 1.0000
14.750 1.2978 0.06065 0.05527 -0.0247 0.0046 1.0000
15.000 1.2966 0.06401 0.05873 -0.0251 0.0046 1.0000
15.250 1.2960 0.06740 0.06223 -0.0258 0.0045 1.0000
15.500 1.2916 0.07141 0.06636 -0.0266 0.0044 1.0000
15.750 1.2897 0.07518 0.07023 -0.0277 0.0043 1.0000
16.000 1.2871 0.07918 0.07433 -0.0289 0.0043 1.0000
16.250 1.2842 0.08334 0.07861 -0.0303 0.0043 1.0000
16.500 1.2777 0.08813 0.08351 -0.0320 0.0041 1.0000
16.750 1.2732 0.09275 0.08826 -0.0337 0.0041 1.0000
17.000 1.2677 0.09767 0.09330 -0.0357 0.0041 1.0000
17.250 1.2610 0.10290 0.09866 -0.0379 0.0041 1.0000
17.500 1.2525 0.10855 0.10444 -0.0405 0.0040 1.0000
17.750 1.2452 0.11414 0.11015 -0.0431 0.0040 1.0000
18.000 1.2366 0.12011 0.11625 -0.0461 0.0040 1.0000
18.250 1.2287 0.12611 0.12238 -0.0493 0.0040 1.0000
18.500 1.2198 0.13242 0.12883 -0.0527 0.0040 1.0000
18.750 1.2109 0.13887 0.13541 -0.0564 0.0040 1.0000
19.000 1.2016 0.14555 0.14223 -0.0603 0.0040 1.0000
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Polar data table (+)
Polar graphs
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