E201 (11.88%) (e201-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E201 (11.88%) (e201-il) Reynolds number: 200,000 Max Cl/Cd: 80.37 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e201-il-200000.txt Download as CSV file: xf-e201-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4029 0.08811 0.08477 -0.0505 1.0000 0.0630
-9.000 -0.4256 0.08236 0.07911 -0.0559 1.0000 0.0633
-8.750 -0.4531 0.07870 0.07549 -0.0574 1.0000 0.0633
-8.500 -0.4358 0.07497 0.07187 -0.0525 1.0000 0.0648
-8.250 -0.4377 0.07334 0.07031 -0.0497 1.0000 0.0656
-8.000 -0.4561 0.07043 0.06748 -0.0491 1.0000 0.0660
-7.750 -0.4799 0.06782 0.06493 -0.0472 1.0000 0.0662
-7.500 -0.4654 0.06391 0.06098 -0.0513 0.9954 0.0682
-7.250 -0.4555 0.05267 0.04887 -0.0691 0.9792 0.0772
-7.000 -0.4398 0.03534 0.03037 -0.0734 0.9717 0.0391
-6.750 -0.4130 0.03120 0.02575 -0.0755 0.9620 0.0385
-6.500 -0.3774 0.02724 0.02126 -0.0784 0.9576 0.0376
-6.250 -0.3472 0.02420 0.01773 -0.0794 0.9481 0.0366
-6.000 -0.3077 0.02172 0.01486 -0.0819 0.9441 0.0365
-5.750 -0.2753 0.02002 0.01293 -0.0827 0.9345 0.0371
-5.500 -0.2368 0.01848 0.01122 -0.0846 0.9293 0.0384
-5.250 -0.2054 0.01748 0.01007 -0.0851 0.9183 0.0402
-5.000 -0.1754 0.01607 0.00868 -0.0858 0.9082 0.0441
-4.750 -0.1428 0.01518 0.00772 -0.0866 0.8991 0.0489
-4.500 -0.1157 0.01421 0.00671 -0.0864 0.8869 0.0580
-4.250 -0.0911 0.01299 0.00574 -0.0859 0.8743 0.1181
-4.000 -0.0656 0.01228 0.00533 -0.0857 0.8623 0.1958
-3.750 -0.0401 0.01175 0.00504 -0.0854 0.8512 0.2745
-3.500 -0.0150 0.01130 0.00489 -0.0850 0.8408 0.3709
-3.250 0.0094 0.01110 0.00484 -0.0843 0.8292 0.4469
-3.000 0.0350 0.01099 0.00478 -0.0837 0.8189 0.4959
-2.750 0.0616 0.01093 0.00468 -0.0832 0.8103 0.5355
-2.500 0.0867 0.01085 0.00464 -0.0824 0.8000 0.5710
-2.250 0.1124 0.01080 0.00460 -0.0818 0.7913 0.6056
-2.000 0.1385 0.01075 0.00454 -0.0812 0.7830 0.6371
-1.750 0.1638 0.01070 0.00452 -0.0805 0.7743 0.6679
-1.500 0.1898 0.01065 0.00447 -0.0798 0.7670 0.6999
-1.250 0.2144 0.01060 0.00450 -0.0789 0.7587 0.7332
-1.000 0.2396 0.01054 0.00448 -0.0779 0.7520 0.7695
-0.750 0.2630 0.01049 0.00452 -0.0767 0.7441 0.8102
-0.500 0.2878 0.01045 0.00453 -0.0754 0.7376 0.8561
-0.250 0.3176 0.01046 0.00459 -0.0752 0.7304 0.9046
0.000 0.3606 0.01049 0.00455 -0.0780 0.7238 0.9463
0.250 0.4108 0.01055 0.00453 -0.0826 0.7171 0.9767
0.500 0.4662 0.01056 0.00445 -0.0886 0.7102 0.9978
0.750 0.4907 0.01067 0.00446 -0.0884 0.7039 1.0000
1.000 0.5122 0.01080 0.00453 -0.0874 0.6969 1.0000
1.250 0.5366 0.01095 0.00457 -0.0868 0.6914 1.0000
1.500 0.5589 0.01110 0.00472 -0.0859 0.6841 1.0000
1.750 0.5840 0.01125 0.00480 -0.0854 0.6784 1.0000
2.000 0.6079 0.01144 0.00497 -0.0848 0.6718 1.0000
2.250 0.6329 0.01160 0.00510 -0.0843 0.6655 1.0000
2.500 0.6587 0.01178 0.00525 -0.0839 0.6598 1.0000
2.750 0.6832 0.01195 0.00544 -0.0833 0.6527 1.0000
3.000 0.7102 0.01212 0.00554 -0.0831 0.6472 1.0000
3.250 0.7342 0.01229 0.00578 -0.0824 0.6393 1.0000
3.500 0.7611 0.01243 0.00586 -0.0822 0.6329 1.0000
3.750 0.7854 0.01259 0.00609 -0.0815 0.6247 1.0000
4.000 0.8125 0.01272 0.00618 -0.0813 0.6179 1.0000
4.250 0.8365 0.01286 0.00640 -0.0805 0.6089 1.0000
4.500 0.8632 0.01297 0.00648 -0.0802 0.6011 1.0000
4.750 0.8877 0.01307 0.00666 -0.0795 0.5916 1.0000
5.000 0.9128 0.01319 0.00682 -0.0789 0.5825 1.0000
5.250 0.9391 0.01326 0.00687 -0.0785 0.5734 1.0000
5.500 0.9628 0.01334 0.00705 -0.0776 0.5623 1.0000
5.750 0.9872 0.01342 0.00721 -0.0768 0.5511 1.0000
6.000 1.0117 0.01348 0.00732 -0.0761 0.5396 1.0000
6.250 1.0357 0.01354 0.00742 -0.0752 0.5268 1.0000
6.500 1.0585 0.01360 0.00755 -0.0741 0.5115 1.0000
6.750 1.0806 0.01368 0.00772 -0.0729 0.4939 1.0000
7.000 1.1021 0.01379 0.00787 -0.0717 0.4737 1.0000
7.250 1.1219 0.01396 0.00805 -0.0701 0.4469 1.0000
7.500 1.1387 0.01426 0.00827 -0.0680 0.4084 1.0000
7.750 1.1509 0.01487 0.00866 -0.0654 0.3530 1.0000
8.000 1.1581 0.01587 0.00930 -0.0621 0.2883 1.0000
8.250 1.1631 0.01708 0.01017 -0.0588 0.2318 1.0000
8.500 1.1682 0.01829 0.01113 -0.0556 0.1862 1.0000
8.750 1.1724 0.01946 0.01209 -0.0522 0.1489 1.0000
9.000 1.1736 0.02071 0.01315 -0.0485 0.1161 1.0000
9.250 1.1725 0.02221 0.01441 -0.0448 0.0812 1.0000
9.500 1.1658 0.02417 0.01613 -0.0407 0.0533 1.0000
9.750 1.1609 0.02621 0.01813 -0.0371 0.0389 1.0000
10.000 1.1566 0.02833 0.02026 -0.0341 0.0340 1.0000
10.250 1.1596 0.03008 0.02212 -0.0320 0.0311 1.0000
10.500 1.1622 0.03196 0.02408 -0.0302 0.0290 1.0000
10.750 1.1636 0.03404 0.02622 -0.0285 0.0274 1.0000
11.000 1.1617 0.03659 0.02879 -0.0267 0.0262 1.0000
11.250 1.1680 0.03853 0.03081 -0.0253 0.0254 1.0000
11.500 1.1765 0.04027 0.03268 -0.0243 0.0240 1.0000
11.750 1.1854 0.04207 0.03457 -0.0232 0.0232 1.0000
12.000 1.1936 0.04394 0.03651 -0.0223 0.0221 1.0000
12.250 1.2034 0.04585 0.03852 -0.0212 0.0214 1.0000
12.500 1.2148 0.04782 0.04052 -0.0202 0.0207 1.0000
12.750 1.2303 0.04991 0.04269 -0.0191 0.0202 1.0000
13.000 1.2481 0.05250 0.04544 -0.0180 0.0199 1.0000
13.250 1.2606 0.05569 0.04887 -0.0171 0.0198 1.0000
13.500 1.2640 0.05916 0.05258 -0.0163 0.0197 1.0000
13.750 1.2643 0.06283 0.05649 -0.0157 0.0197 1.0000
14.000 1.2606 0.06633 0.06024 -0.0154 0.0198 1.0000
14.250 1.2539 0.07012 0.06426 -0.0153 0.0198 1.0000
14.500 1.2452 0.07402 0.06839 -0.0155 0.0199 1.0000
14.750 1.2345 0.07819 0.07278 -0.0162 0.0200 1.0000
15.000 1.2205 0.08292 0.07776 -0.0174 0.0202 1.0000
15.250 1.2033 0.08833 0.08344 -0.0192 0.0204 1.0000
15.500 1.1795 0.09531 0.09076 -0.0221 0.0209 1.0000
15.750 1.1461 0.10455 0.10034 -0.0269 0.0213 1.0000
16.000 1.1091 0.11557 0.11170 -0.0335 0.0219 1.0000
16.250 1.0738 0.12767 0.12406 -0.0412 0.0224 1.0000
16.500 1.0351 0.14240 0.13899 -0.0511 0.0230 1.0000
16.750 0.9890 0.16247 0.15918 -0.0637 0.0244 1.0000
17.000 0.9754 0.17271 0.16937 -0.0691 0.0255 1.0000
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Polar data table (+)
Polar graphs
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