EPPLER 1200 AIRFOIL (e1200-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1200 AIRFOIL (e1200-il) Reynolds number: 100,000 Max Cl/Cd: 46.86 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1200-il-100000.txt Download as CSV file: xf-e1200-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1200 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2805 0.10343 0.09889 -0.0689 0.9603 0.1629
-9.250 -0.3103 0.09778 0.09333 -0.0760 0.9561 0.1719
-9.000 -0.2936 0.09567 0.09121 -0.0739 0.9525 0.1741
-8.750 -0.2897 0.09315 0.08870 -0.0735 0.9478 0.1772
-8.250 -0.5717 0.06248 0.05672 -0.0785 0.9276 0.0805
-8.000 -0.5594 0.05844 0.05248 -0.0793 0.9252 0.0794
-7.750 -0.5717 0.05657 0.05048 -0.0748 0.9220 0.0784
-7.500 -0.5751 0.05383 0.04748 -0.0720 0.9191 0.0770
-7.250 -0.5703 0.05053 0.04376 -0.0704 0.9161 0.0750
-7.000 -0.5601 0.04671 0.03922 -0.0693 0.9136 0.0723
-6.750 -0.5417 0.04425 0.03618 -0.0688 0.9118 0.0713
-6.500 -0.5148 0.04231 0.03394 -0.0694 0.9099 0.0717
-6.250 -0.4981 0.04104 0.03249 -0.0682 0.9073 0.0726
-6.000 -0.4866 0.04014 0.03149 -0.0661 0.9046 0.0741
-5.750 -0.4704 0.03934 0.03055 -0.0648 0.9027 0.0766
-5.500 -0.4508 0.03850 0.02951 -0.0638 0.9006 0.0789
-5.250 -0.4257 0.03766 0.02844 -0.0635 0.8978 0.0810
-5.000 -0.3962 0.03651 0.02736 -0.0641 0.8951 0.0843
-4.750 -0.3626 0.03600 0.02686 -0.0653 0.8928 0.0907
-4.500 -0.3526 0.03557 0.02640 -0.0629 0.8905 0.0958
-4.250 -0.3412 0.03509 0.02606 -0.0608 0.8877 0.1035
-4.000 -0.3249 0.03452 0.02561 -0.0595 0.8855 0.1157
-3.750 -0.3049 0.03374 0.02509 -0.0589 0.8829 0.1488
-3.500 -0.2776 0.03195 0.02442 -0.0604 0.8795 0.2955
-3.250 -0.2514 0.03171 0.02574 -0.0595 0.8763 0.5834
-3.000 -0.2471 0.03258 0.02664 -0.0552 0.8734 0.6420
-2.750 -0.2408 0.03359 0.02761 -0.0509 0.8701 0.6840
-2.500 -0.2350 0.03473 0.02879 -0.0457 0.8675 0.7120
-2.250 -0.2199 0.03571 0.02970 -0.0424 0.8636 0.7369
-2.000 -0.1940 0.03691 0.03081 -0.0400 0.8586 0.7586
-1.750 -0.1966 0.03723 0.03111 -0.0349 0.8549 0.7737
-1.500 -0.1898 0.03772 0.03155 -0.0311 0.8511 0.7899
-1.250 -0.1742 0.03826 0.03201 -0.0282 0.8465 0.8068
-1.000 -0.1565 0.03873 0.03240 -0.0256 0.8392 0.8229
-0.750 -0.1497 0.03894 0.03255 -0.0223 0.8338 0.8369
-0.500 -0.1212 0.03938 0.03289 -0.0211 0.8271 0.8532
-0.250 -0.1210 0.03943 0.03291 -0.0166 0.8192 0.8682
0.000 -0.1093 0.03956 0.03300 -0.0128 0.8128 0.8869
0.250 -0.0975 0.03963 0.03302 -0.0093 0.8040 0.9054
0.500 -0.0766 0.03974 0.03306 -0.0080 0.7964 0.9196
0.750 -0.0513 0.03990 0.03313 -0.0082 0.7868 0.9288
1.000 -0.0137 0.04016 0.03330 -0.0103 0.7788 0.9354
1.250 0.0092 0.04036 0.03343 -0.0106 0.7688 0.9427
1.500 0.0556 0.04067 0.03364 -0.0141 0.7615 0.9476
1.750 0.0794 0.04097 0.03390 -0.0147 0.7507 0.9544
2.000 0.1323 0.04117 0.03400 -0.0190 0.7443 0.9586
2.250 0.1595 0.04163 0.03445 -0.0206 0.7327 0.9646
2.500 0.2162 0.04163 0.03437 -0.0251 0.7273 0.9686
2.750 0.2456 0.04212 0.03485 -0.0272 0.7149 0.9741
3.000 0.3083 0.04188 0.03455 -0.0323 0.7105 0.9774
3.250 0.3367 0.04234 0.03503 -0.0343 0.6975 0.9839
3.500 0.4010 0.04176 0.03441 -0.0393 0.6939 0.9865
3.750 0.4283 0.04219 0.03486 -0.0411 0.6807 0.9953
4.000 0.4863 0.04133 0.03398 -0.0450 0.6771 1.0000
4.250 0.4762 0.04132 0.03397 -0.0403 0.6637 1.0000
4.500 0.4872 0.04149 0.03413 -0.0388 0.6512 1.0000
4.750 0.5365 0.04043 0.03307 -0.0411 0.6474 1.0000
5.000 0.5552 0.04065 0.03330 -0.0409 0.6347 1.0000
5.250 0.6077 0.03927 0.03193 -0.0434 0.6315 1.0000
5.500 0.6296 0.03941 0.03211 -0.0435 0.6186 1.0000
5.750 0.6840 0.03766 0.03038 -0.0459 0.6160 1.0000
7.000 0.9041 0.03005 0.02301 -0.0525 0.5822 1.0000
7.250 0.9418 0.02886 0.02187 -0.0533 0.5700 1.0000
7.500 0.9810 0.02761 0.02065 -0.0541 0.5558 1.0000
7.750 1.0273 0.02610 0.01913 -0.0556 0.5396 1.0000
8.000 1.0732 0.02486 0.01780 -0.0573 0.5189 1.0000
8.250 1.1030 0.02463 0.01746 -0.0574 0.4929 1.0000
8.500 1.1335 0.02464 0.01726 -0.0577 0.4665 1.0000
8.750 1.1645 0.02485 0.01721 -0.0581 0.4413 1.0000
9.000 1.1825 0.02565 0.01789 -0.0573 0.4185 1.0000
9.250 1.2028 0.02644 0.01852 -0.0567 0.3980 1.0000
9.500 1.2241 0.02725 0.01918 -0.0562 0.3797 1.0000
9.750 1.2439 0.02814 0.01996 -0.0557 0.3633 1.0000
10.000 1.2620 0.02909 0.02085 -0.0549 0.3483 1.0000
10.250 1.2797 0.03008 0.02178 -0.0542 0.3345 1.0000
10.500 1.2991 0.03105 0.02269 -0.0536 0.3219 1.0000
10.750 1.3227 0.03196 0.02350 -0.0536 0.3097 1.0000
11.000 1.3356 0.03305 0.02462 -0.0523 0.2986 1.0000
11.250 1.3501 0.03420 0.02582 -0.0513 0.2884 1.0000
11.500 1.3750 0.03515 0.02665 -0.0514 0.2778 1.0000
11.750 1.3818 0.03642 0.02805 -0.0495 0.2687 1.0000
12.000 1.4005 0.03758 0.02920 -0.0490 0.2596 1.0000
12.250 1.4141 0.03873 0.03039 -0.0480 0.2508 1.0000
12.500 1.4260 0.04011 0.03184 -0.0469 0.2428 1.0000
12.750 1.4417 0.04125 0.03298 -0.0461 0.2346 1.0000
13.000 1.4509 0.04279 0.03465 -0.0448 0.2273 1.0000
13.250 1.4613 0.04411 0.03602 -0.0436 0.2199 1.0000
13.500 1.4745 0.04561 0.03757 -0.0427 0.2129 1.0000
13.750 1.4752 0.04736 0.03950 -0.0408 0.2067 1.0000
14.000 1.4999 0.04847 0.04051 -0.0410 0.1993 1.0000
14.250 1.4888 0.05081 0.04314 -0.0384 0.1943 1.0000
14.500 1.5091 0.05183 0.04410 -0.0382 0.1875 1.0000
14.750 1.5076 0.05416 0.04663 -0.0366 0.1824 1.0000
15.000 1.4984 0.05671 0.04942 -0.0346 0.1777 1.0000
15.250 1.5336 0.05719 0.04967 -0.0354 0.1704 1.0000
15.500 1.5102 0.06067 0.05353 -0.0329 0.1673 1.0000
15.750 1.4967 0.06384 0.05695 -0.0313 0.1632 1.0000
16.000 1.5369 0.06375 0.05659 -0.0321 0.1560 1.0000
16.250 1.5074 0.06809 0.06132 -0.0301 0.1538 1.0000
16.500 1.4828 0.07259 0.06614 -0.0289 0.1509 1.0000
16.750 1.4692 0.07637 0.07014 -0.0284 0.1474 1.0000
17.000 1.5055 0.07606 0.06962 -0.0285 0.1412 1.0000
17.250 1.4676 0.08226 0.07619 -0.0281 0.1398 1.0000
17.500 1.4258 0.08972 0.08402 -0.0288 0.1384 1.0000
17.750 1.3690 0.10008 0.09472 -0.0314 0.1379 1.0000
18.250 1.3943 0.10298 0.09765 -0.0317 0.1292 1.0000
18.500 1.3390 0.11454 0.10949 -0.0361 0.1287 1.0000
18.750 0.9313 0.21753 0.21233 -0.0965 0.1746 1.0000
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Polar data table (+)
Polar graphs
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