E212 (10.55%) (e212-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E212 (10.55%) (e212-il) Reynolds number: 100,000 Max Cl/Cd: 59.92 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e212-il-100000.txt Download as CSV file: xf-e212-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E212 (10.55%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4094 0.10194 0.09692 -0.0316 1.0000 0.1230
-8.750 -0.4162 0.09914 0.09420 -0.0325 1.0000 0.1274
-8.500 -0.4771 0.09793 0.09329 -0.0375 1.0000 0.1303
-8.250 -0.4285 0.09267 0.08789 -0.0326 1.0000 0.1334
-8.000 -0.4235 0.09017 0.08542 -0.0310 1.0000 0.1370
-7.750 -0.4352 0.08766 0.08301 -0.0306 1.0000 0.1410
-7.500 -0.4956 0.08437 0.08000 -0.0376 1.0000 0.1445
-7.250 -0.5309 0.06010 0.05547 -0.0522 1.0000 0.0721
-7.000 -0.5455 0.04815 0.04273 -0.0596 1.0000 0.0608
-6.750 -0.5349 0.04320 0.03745 -0.0609 1.0000 0.0587
-6.500 -0.5183 0.03788 0.03155 -0.0629 1.0000 0.0566
-6.250 -0.4967 0.03420 0.02732 -0.0642 1.0000 0.0573
-6.000 -0.4725 0.03124 0.02383 -0.0651 1.0000 0.0587
-5.750 -0.4463 0.02858 0.02067 -0.0656 1.0000 0.0595
-5.500 -0.4192 0.02639 0.01806 -0.0658 1.0000 0.0608
-5.250 -0.3925 0.02463 0.01594 -0.0657 1.0000 0.0629
-5.000 -0.3673 0.02285 0.01424 -0.0657 1.0000 0.0674
-4.750 -0.3415 0.02170 0.01297 -0.0655 1.0000 0.0764
-4.500 -0.3146 0.02034 0.01177 -0.0658 1.0000 0.0939
-4.250 -0.2837 0.01870 0.01052 -0.0672 1.0000 0.1628
-4.000 -0.2574 0.01831 0.01029 -0.0679 1.0000 0.2327
-3.750 -0.2326 0.01807 0.01026 -0.0680 1.0000 0.2865
-3.500 -0.2082 0.01786 0.01015 -0.0679 1.0000 0.3317
-3.250 -0.1845 0.01775 0.01012 -0.0676 1.0000 0.3742
-3.000 -0.1612 0.01773 0.01014 -0.0672 1.0000 0.4158
-2.750 -0.1392 0.01775 0.01029 -0.0665 1.0000 0.4526
-2.500 -0.1172 0.01782 0.01043 -0.0658 1.0000 0.4896
-2.250 -0.0961 0.01794 0.01060 -0.0650 1.0000 0.5250
-2.000 -0.0758 0.01809 0.01084 -0.0640 1.0000 0.5583
-1.750 -0.0561 0.01828 0.01113 -0.0630 1.0000 0.5917
-1.500 -0.0183 0.01870 0.01159 -0.0652 0.9933 0.6332
-1.250 0.0224 0.01911 0.01208 -0.0677 0.9849 0.6737
-1.000 0.0595 0.01934 0.01239 -0.0694 0.9750 0.7123
-0.750 0.0941 0.01952 0.01262 -0.0706 0.9648 0.7502
-0.500 0.1273 0.01963 0.01279 -0.0713 0.9546 0.7885
-0.250 0.1609 0.01968 0.01289 -0.0720 0.9451 0.8297
0.000 0.1893 0.01954 0.01282 -0.0714 0.9345 0.8743
0.250 0.2148 0.01918 0.01256 -0.0704 0.9225 0.9383
0.500 0.2671 0.01900 0.01230 -0.0760 0.9115 1.0000
0.750 0.3242 0.01895 0.01212 -0.0821 0.9049 1.0000
1.000 0.3656 0.01891 0.01200 -0.0851 0.8928 1.0000
1.250 0.4076 0.01883 0.01187 -0.0880 0.8814 1.0000
1.500 0.4618 0.01843 0.01145 -0.0925 0.8750 1.0000
1.750 0.5016 0.01820 0.01121 -0.0945 0.8628 1.0000
2.000 0.5434 0.01788 0.01089 -0.0967 0.8512 1.0000
2.250 0.5906 0.01742 0.01047 -0.0996 0.8413 1.0000
2.500 0.6393 0.01684 0.00993 -0.1026 0.8315 1.0000
2.750 0.6791 0.01647 0.00960 -0.1040 0.8174 1.0000
3.000 0.7193 0.01609 0.00925 -0.1055 0.8021 1.0000
3.250 0.7575 0.01578 0.00898 -0.1065 0.7850 1.0000
3.500 0.7887 0.01568 0.00890 -0.1064 0.7636 1.0000
3.750 0.8238 0.01551 0.00872 -0.1069 0.7425 1.0000
4.000 0.8530 0.01553 0.00876 -0.1065 0.7180 1.0000
4.250 0.8834 0.01556 0.00876 -0.1062 0.6931 1.0000
4.500 0.9114 0.01569 0.00883 -0.1055 0.6661 1.0000
4.750 0.9369 0.01589 0.00902 -0.1045 0.6371 1.0000
5.000 0.9617 0.01615 0.00922 -0.1034 0.6070 1.0000
5.250 0.9857 0.01646 0.00946 -0.1021 0.5760 1.0000
5.500 1.0084 0.01683 0.00977 -0.1007 0.5436 1.0000
5.750 1.0297 0.01725 0.01014 -0.0992 0.5094 1.0000
6.000 1.0503 0.01773 0.01054 -0.0975 0.4744 1.0000
6.250 1.0702 0.01829 0.01095 -0.0958 0.4389 1.0000
6.500 1.0883 0.01889 0.01151 -0.0939 0.4003 1.0000
6.750 1.1057 0.01961 0.01208 -0.0919 0.3623 1.0000
7.000 1.1219 0.02040 0.01276 -0.0898 0.3227 1.0000
7.250 1.1373 0.02135 0.01356 -0.0877 0.2840 1.0000
7.500 1.1513 0.02242 0.01443 -0.0855 0.2465 1.0000
7.750 1.1641 0.02351 0.01541 -0.0832 0.2086 1.0000
8.000 1.1747 0.02465 0.01633 -0.0808 0.1734 1.0000
8.250 1.1859 0.02591 0.01748 -0.0785 0.1395 1.0000
8.500 1.1945 0.02754 0.01896 -0.0758 0.1090 1.0000
8.750 1.1996 0.02968 0.02092 -0.0726 0.0828 1.0000
9.000 1.2071 0.03189 0.02300 -0.0697 0.0682 1.0000
9.250 1.2212 0.03399 0.02514 -0.0677 0.0591 1.0000
9.500 1.2397 0.03641 0.02753 -0.0668 0.0533 1.0000
9.750 1.2628 0.03873 0.03007 -0.0660 0.0495 1.0000
10.000 1.2859 0.04127 0.03272 -0.0656 0.0469 1.0000
10.250 1.3135 0.04497 0.03648 -0.0661 0.0449 1.0000
10.500 1.3310 0.04903 0.04088 -0.0651 0.0441 1.0000
10.750 1.3361 0.05193 0.04422 -0.0624 0.0435 1.0000
11.000 1.3356 0.05493 0.04765 -0.0593 0.0429 1.0000
11.250 1.3291 0.05792 0.05105 -0.0558 0.0425 1.0000
11.500 1.3186 0.06111 0.05459 -0.0523 0.0421 1.0000
11.750 1.3050 0.06461 0.05841 -0.0492 0.0420 1.0000
12.000 1.2886 0.06846 0.06258 -0.0468 0.0419 1.0000
12.250 1.2700 0.07277 0.06717 -0.0452 0.0421 1.0000
12.500 1.2494 0.07758 0.07225 -0.0446 0.0422 1.0000
12.750 1.2274 0.08297 0.07789 -0.0451 0.0425 1.0000
13.000 1.2043 0.08902 0.08416 -0.0468 0.0428 1.0000
13.250 1.1808 0.09575 0.09105 -0.0496 0.0432 1.0000
13.500 1.1581 0.10317 0.09864 -0.0533 0.0436 1.0000
13.750 1.1375 0.11111 0.10669 -0.0576 0.0441 1.0000
14.000 0.8630 0.13633 0.13273 -0.0716 0.0543 1.0000
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Polar data table (+)
Polar graphs
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