EPPLER E1212 AIRFOIL (e1212-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E1212 AIRFOIL (e1212-il) Reynolds number: 50,000 Max Cl/Cd: 23.18 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1212-il-50000-n5.txt Download as CSV file: xf-e1212-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E1212 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3844 0.10498 0.09704 -0.0305 1.0000 0.1449
-11.000 -0.3710 0.10333 0.09541 -0.0302 1.0000 0.1489
-10.750 -0.3801 0.09876 0.09087 -0.0324 1.0000 0.1538
-10.500 -0.3821 0.09512 0.08727 -0.0337 1.0000 0.1577
-10.250 -0.3698 0.09349 0.08566 -0.0334 1.0000 0.1617
-10.000 -0.3826 0.08875 0.08097 -0.0356 1.0000 0.1667
-9.750 -0.3916 0.08452 0.07680 -0.0373 1.0000 0.1709
-9.500 -0.3776 0.08336 0.07568 -0.0364 1.0000 0.1746
-9.250 -0.3893 0.07920 0.07160 -0.0380 1.0000 0.1793
-9.000 -0.4343 0.07153 0.06406 -0.0419 1.0000 0.1844
-8.750 -0.4162 0.07149 0.06409 -0.0398 1.0000 0.1875
-8.500 -0.4341 0.06807 0.06080 -0.0398 1.0000 0.1913
-8.250 -0.5322 0.05798 0.05083 -0.0421 1.0000 0.1960
-8.000 -0.5194 0.05433 0.04706 -0.0465 0.9782 0.2017
-7.750 -0.4854 0.05259 0.04521 -0.0501 0.9535 0.2075
-7.500 -0.4780 0.04652 0.03865 -0.0568 0.9269 0.2163
-7.250 -0.4336 0.04610 0.03823 -0.0591 0.9089 0.2212
-7.000 -0.4098 0.04299 0.03471 -0.0628 0.8882 0.2289
-6.750 -0.3813 0.04099 0.03245 -0.0651 0.8687 0.2348
-6.500 -0.3479 0.04023 0.03161 -0.0661 0.8497 0.2399
-6.250 -0.3258 0.03838 0.02939 -0.0671 0.8307 0.2465
-6.000 -0.3032 0.03691 0.02761 -0.0675 0.8127 0.2522
-5.750 -0.2758 0.03637 0.02698 -0.0672 0.7957 0.2567
-5.500 -0.2526 0.03545 0.02584 -0.0668 0.7791 0.2622
-5.250 -0.2343 0.03406 0.02398 -0.0666 0.7626 0.2690
-5.000 -0.2090 0.03364 0.02358 -0.0658 0.7471 0.2728
-4.750 -0.1841 0.03312 0.02291 -0.0651 0.7332 0.2777
-4.500 -0.1614 0.03241 0.02198 -0.0645 0.7187 0.2838
-4.250 -0.1388 0.03164 0.02093 -0.0641 0.7049 0.2896
-4.000 -0.1128 0.03124 0.02047 -0.0633 0.6930 0.2940
-3.750 -0.0893 0.03085 0.02000 -0.0626 0.6790 0.2996
-3.500 -0.0648 0.03031 0.01919 -0.0622 0.6673 0.3061
-3.250 -0.0398 0.02987 0.01863 -0.0616 0.6553 0.3113
-3.000 -0.0146 0.02960 0.01835 -0.0610 0.6433 0.3166
-2.750 0.0118 0.02925 0.01781 -0.0605 0.6328 0.3233
-2.500 0.0368 0.02893 0.01733 -0.0602 0.6210 0.3299
-2.250 0.0636 0.02866 0.01702 -0.0596 0.6112 0.3354
-2.000 0.0885 0.02851 0.01683 -0.0591 0.5998 0.3422
-1.750 0.1159 0.02824 0.01633 -0.0588 0.5907 0.3502
-1.500 0.1406 0.02814 0.01631 -0.0582 0.5797 0.3563
-1.250 0.1678 0.02796 0.01601 -0.0578 0.5707 0.3642
-1.000 0.1934 0.02792 0.01591 -0.0574 0.5606 0.3726
-0.750 0.2196 0.02781 0.01579 -0.0568 0.5517 0.3809
-0.500 0.2454 0.02781 0.01569 -0.0564 0.5425 0.3911
-0.250 0.2711 0.02777 0.01570 -0.0558 0.5333 0.4002
0.000 0.2983 0.02775 0.01555 -0.0554 0.5258 0.4126
0.250 0.3221 0.02785 0.01578 -0.0548 0.5161 0.4241
0.500 0.3496 0.02776 0.01562 -0.0543 0.5091 0.4388
0.750 0.3728 0.02797 0.01592 -0.0537 0.5000 0.4547
1.000 0.3981 0.02798 0.01600 -0.0530 0.4924 0.4733
1.250 0.4233 0.02802 0.01610 -0.0523 0.4855 0.4958
1.500 0.4451 0.02824 0.01650 -0.0514 0.4768 0.5217
1.750 0.4701 0.02816 0.01654 -0.0504 0.4705 0.5555
2.000 0.4906 0.02837 0.01700 -0.0490 0.4631 0.5979
2.250 0.5105 0.02847 0.01739 -0.0473 0.4558 0.6544
2.500 0.5342 0.02827 0.01743 -0.0455 0.4503 0.7375
2.750 0.5669 0.02859 0.01812 -0.0460 0.4416 0.8690
3.000 0.6134 0.02890 0.01832 -0.0496 0.4339 1.0000
3.250 0.6390 0.02921 0.01838 -0.0491 0.4288 1.0000
3.500 0.6540 0.03018 0.01937 -0.0479 0.4208 1.0000
3.750 0.6772 0.03064 0.01969 -0.0472 0.4150 1.0000
4.000 0.7051 0.03087 0.01969 -0.0469 0.4106 1.0000
4.250 0.7161 0.03216 0.02109 -0.0454 0.4028 1.0000
4.500 0.7377 0.03275 0.02160 -0.0445 0.3970 1.0000
4.750 0.7653 0.03301 0.02167 -0.0442 0.3927 1.0000
5.000 0.7754 0.03441 0.02317 -0.0426 0.3859 1.0000
5.250 0.7921 0.03536 0.02412 -0.0415 0.3800 1.0000
5.500 0.8179 0.03573 0.02437 -0.0410 0.3756 1.0000
5.750 0.8347 0.03673 0.02535 -0.0400 0.3706 1.0000
6.000 0.8380 0.03858 0.02734 -0.0381 0.3641 1.0000
6.250 0.8575 0.03936 0.02807 -0.0372 0.3594 1.0000
6.500 0.8877 0.03949 0.02807 -0.0370 0.3559 1.0000
6.750 0.8749 0.04239 0.03117 -0.0343 0.3494 1.0000
7.000 0.8726 0.04458 0.03344 -0.0324 0.3438 1.0000
7.250 0.8947 0.04519 0.03399 -0.0317 0.3401 1.0000
7.500 0.9302 0.04503 0.03372 -0.0317 0.3374 1.0000
7.750 0.8008 0.05715 0.04624 -0.0276 0.3249 1.0000
8.000 0.8244 0.05753 0.04657 -0.0268 0.3220 1.0000
8.250 0.8606 0.05671 0.04568 -0.0258 0.3201 1.0000
8.750 0.7746 0.07341 0.06257 -0.0299 0.3027 1.0000
9.250 0.7242 0.08745 0.07671 -0.0344 0.2877 1.0000
9.500 0.7450 0.08834 0.07758 -0.0338 0.2858 1.0000
9.750 0.7004 0.09817 0.08750 -0.0377 0.2775 1.0000
10.000 0.7066 0.10104 0.09037 -0.0382 0.2735 1.0000
10.250 0.7223 0.10271 0.09205 -0.0380 0.2709 1.0000
10.500 0.7408 0.10409 0.09342 -0.0377 0.2691 1.0000
10.750 0.7087 0.11240 0.10181 -0.0413 0.2629 1.0000
11.000 0.7099 0.11608 0.10551 -0.0424 0.2588 1.0000
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Polar data table (+)
Polar graphs
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