E212 (10.55%) (e212-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E212 (10.55%) (e212-il) Reynolds number: 100,000 Max Cl/Cd: 58.75 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e212-il-100000-n5.txt Download as CSV file: xf-e212-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4625 0.09346 0.08826 -0.0406 1.0000 0.0247
-9.750 -0.4976 0.08040 0.07529 -0.0466 1.0000 0.0236
-9.500 -0.5136 0.07403 0.06897 -0.0493 1.0000 0.0233
-9.250 -0.5365 0.06706 0.06203 -0.0529 1.0000 0.0231
-9.000 -0.5618 0.06161 0.05663 -0.0553 1.0000 0.0228
-8.750 -0.5866 0.05652 0.05148 -0.0584 1.0000 0.0226
-8.500 -0.6032 0.05149 0.04623 -0.0607 1.0000 0.0225
-8.250 -0.6107 0.04686 0.04128 -0.0621 1.0000 0.0225
-8.000 -0.6094 0.04264 0.03666 -0.0631 1.0000 0.0225
-7.750 -0.6008 0.03885 0.03239 -0.0638 1.0000 0.0226
-7.500 -0.5868 0.03553 0.02855 -0.0644 1.0000 0.0232
-7.250 -0.5690 0.03288 0.02544 -0.0647 1.0000 0.0239
-7.000 -0.5502 0.03111 0.02357 -0.0647 1.0000 0.0249
-6.750 -0.5294 0.02944 0.02168 -0.0647 1.0000 0.0258
-6.500 -0.5074 0.02772 0.01972 -0.0646 1.0000 0.0265
-6.250 -0.4844 0.02617 0.01792 -0.0645 1.0000 0.0274
-6.000 -0.4608 0.02484 0.01641 -0.0643 1.0000 0.0283
-5.750 -0.4367 0.02368 0.01506 -0.0642 1.0000 0.0294
-5.500 -0.4080 0.02251 0.01381 -0.0652 0.9988 0.0312
-5.250 -0.3722 0.02164 0.01282 -0.0675 0.9955 0.0350
-5.000 -0.3366 0.02069 0.01177 -0.0698 0.9920 0.0412
-4.750 -0.3001 0.01969 0.01072 -0.0721 0.9884 0.0538
-4.500 -0.2627 0.01875 0.00992 -0.0748 0.9853 0.0919
-4.250 -0.2284 0.01806 0.00951 -0.0770 0.9809 0.1550
-4.000 -0.1927 0.01760 0.00926 -0.0793 0.9763 0.2149
-3.750 -0.1562 0.01731 0.00901 -0.0815 0.9721 0.2576
-3.500 -0.1232 0.01703 0.00877 -0.0828 0.9661 0.2964
-3.250 -0.0860 0.01683 0.00860 -0.0849 0.9616 0.3363
-3.000 -0.0544 0.01662 0.00844 -0.0859 0.9547 0.3710
-2.750 -0.0181 0.01646 0.00828 -0.0877 0.9496 0.4067
-2.500 0.0136 0.01630 0.00815 -0.0885 0.9425 0.4397
-2.250 0.0488 0.01614 0.00803 -0.0900 0.9366 0.4729
-2.000 0.0812 0.01600 0.00791 -0.0908 0.9295 0.5038
-1.750 0.1155 0.01585 0.00780 -0.0920 0.9229 0.5344
-1.500 0.1484 0.01570 0.00770 -0.0928 0.9159 0.5635
-1.250 0.1816 0.01555 0.00759 -0.0936 0.9086 0.5921
-1.000 0.2146 0.01539 0.00748 -0.0944 0.9015 0.6203
-0.750 0.2476 0.01522 0.00735 -0.0950 0.8939 0.6483
-0.500 0.2798 0.01506 0.00724 -0.0955 0.8858 0.6757
-0.250 0.3134 0.01488 0.00712 -0.0962 0.8782 0.7029
0.000 0.3433 0.01474 0.00704 -0.0961 0.8684 0.7294
0.250 0.3788 0.01452 0.00687 -0.0970 0.8612 0.7571
0.500 0.4059 0.01440 0.00680 -0.0964 0.8494 0.7839
0.750 0.4338 0.01423 0.00670 -0.0957 0.8380 0.8111
1.000 0.4628 0.01403 0.00655 -0.0953 0.8269 0.8398
1.250 0.4921 0.01380 0.00636 -0.0948 0.8154 0.8710
1.500 0.5189 0.01359 0.00621 -0.0939 0.8013 0.9085
1.750 0.5548 0.01336 0.00601 -0.0951 0.7865 0.9680
2.000 0.5913 0.01330 0.00590 -0.0967 0.7704 1.0000
2.250 0.6241 0.01335 0.00591 -0.0976 0.7525 1.0000
2.500 0.6565 0.01341 0.00594 -0.0983 0.7336 1.0000
2.750 0.6885 0.01350 0.00597 -0.0989 0.7140 1.0000
3.000 0.7198 0.01362 0.00605 -0.0994 0.6936 1.0000
3.250 0.7486 0.01379 0.00618 -0.0994 0.6709 1.0000
3.500 0.7777 0.01398 0.00630 -0.0995 0.6479 1.0000
3.750 0.8049 0.01421 0.00650 -0.0992 0.6230 1.0000
4.000 0.8316 0.01447 0.00670 -0.0988 0.5976 1.0000
4.250 0.8578 0.01477 0.00693 -0.0983 0.5716 1.0000
4.500 0.8829 0.01510 0.00719 -0.0977 0.5441 1.0000
4.750 0.9074 0.01545 0.00752 -0.0969 0.5159 1.0000
5.000 0.9312 0.01585 0.00785 -0.0961 0.4866 1.0000
5.250 0.9543 0.01629 0.00822 -0.0951 0.4566 1.0000
5.500 0.9768 0.01676 0.00864 -0.0941 0.4262 1.0000
5.750 0.9987 0.01728 0.00909 -0.0930 0.3954 1.0000
6.000 1.0201 0.01783 0.00958 -0.0919 0.3644 1.0000
6.250 1.0407 0.01844 0.01011 -0.0907 0.3328 1.0000
6.500 1.0607 0.01911 0.01071 -0.0894 0.3009 1.0000
6.750 1.0802 0.01983 0.01135 -0.0881 0.2688 1.0000
7.000 1.0992 0.02060 0.01205 -0.0868 0.2378 1.0000
7.250 1.1176 0.02142 0.01280 -0.0854 0.2083 1.0000
7.500 1.1352 0.02233 0.01362 -0.0840 0.1787 1.0000
7.750 1.1515 0.02335 0.01452 -0.0825 0.1466 1.0000
8.000 1.1663 0.02451 0.01547 -0.0809 0.1141 1.0000
8.250 1.1811 0.02570 0.01649 -0.0793 0.0864 1.0000
8.500 1.1961 0.02685 0.01762 -0.0776 0.0668 1.0000
8.750 1.2082 0.02823 0.01894 -0.0756 0.0516 1.0000
9.000 1.2175 0.02972 0.02046 -0.0730 0.0409 1.0000
9.250 1.2255 0.03126 0.02205 -0.0704 0.0345 1.0000
9.500 1.2330 0.03281 0.02372 -0.0678 0.0305 1.0000
9.750 1.2403 0.03434 0.02535 -0.0654 0.0275 1.0000
10.000 1.2448 0.03612 0.02722 -0.0628 0.0256 1.0000
10.250 1.2503 0.03787 0.02917 -0.0605 0.0243 1.0000
10.500 1.2550 0.03976 0.03122 -0.0582 0.0233 1.0000
10.750 1.2590 0.04177 0.03338 -0.0562 0.0224 1.0000
11.000 1.2624 0.04391 0.03567 -0.0544 0.0217 1.0000
11.250 1.2650 0.04622 0.03810 -0.0527 0.0212 1.0000
11.500 1.2666 0.04878 0.04077 -0.0513 0.0207 1.0000
11.750 1.2701 0.05141 0.04356 -0.0500 0.0203 1.0000
12.000 1.2736 0.05417 0.04655 -0.0489 0.0199 1.0000
12.250 1.2755 0.05715 0.04979 -0.0479 0.0195 1.0000
12.500 1.2752 0.06039 0.05327 -0.0473 0.0190 1.0000
12.750 1.2728 0.06391 0.05703 -0.0470 0.0186 1.0000
13.000 1.2685 0.06773 0.06109 -0.0470 0.0182 1.0000
13.250 1.2621 0.07190 0.06549 -0.0476 0.0178 1.0000
13.500 1.2542 0.07646 0.07028 -0.0486 0.0176 1.0000
13.750 1.2446 0.08146 0.07549 -0.0501 0.0173 1.0000
14.000 1.2332 0.08696 0.08122 -0.0523 0.0172 1.0000
14.250 1.2201 0.09311 0.08762 -0.0551 0.0171 1.0000
14.500 1.2048 0.10005 0.09480 -0.0588 0.0171 1.0000
14.750 1.1866 0.10806 0.10304 -0.0635 0.0171 1.0000
15.000 1.1644 0.11764 0.11288 -0.0695 0.0173 1.0000
15.250 1.1354 0.12988 0.12538 -0.0777 0.0178 1.0000
15.500 1.0937 0.14748 0.14324 -0.0895 0.0188 1.0000
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Polar data table (+)
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