EPPLER 1200 AIRFOIL (e1200-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER 1200 AIRFOIL (e1200-il) Reynolds number: 100,000 Max Cl/Cd: 39.54 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1200-il-100000-n5.txt Download as CSV file: xf-e1200-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3140 0.09878 0.09362 -0.0835 0.9625 0.0351
-12.000 -0.3354 0.08611 0.08091 -0.0922 0.9570 0.0346
-11.750 -0.3836 0.07012 0.06471 -0.1059 0.9480 0.0337
-11.500 -0.4143 0.06059 0.05483 -0.1152 0.9400 0.0331
-11.250 -0.4317 0.05496 0.04887 -0.1198 0.9297 0.0333
-11.000 -0.4422 0.05048 0.04404 -0.1228 0.9205 0.0334
-10.750 -0.4481 0.04711 0.04033 -0.1241 0.9113 0.0338
-10.500 -0.4549 0.04456 0.03745 -0.1232 0.9012 0.0342
-10.250 -0.4564 0.04213 0.03465 -0.1222 0.8939 0.0347
-10.000 -0.4548 0.04011 0.03229 -0.1206 0.8865 0.0350
-9.750 -0.4458 0.03813 0.02997 -0.1195 0.8806 0.0353
-9.500 -0.4300 0.03613 0.02759 -0.1192 0.8766 0.0358
-9.250 -0.4166 0.03475 0.02608 -0.1179 0.8707 0.0363
-9.000 -0.3988 0.03351 0.02475 -0.1172 0.8657 0.0369
-8.750 -0.3773 0.03228 0.02340 -0.1170 0.8620 0.0377
-8.500 -0.3541 0.03118 0.02215 -0.1170 0.8592 0.0391
-8.250 -0.3404 0.03046 0.02132 -0.1152 0.8538 0.0404
-8.000 -0.3211 0.02960 0.02027 -0.1142 0.8496 0.0421
-7.750 -0.2992 0.02863 0.01928 -0.1137 0.8462 0.0434
-7.500 -0.2760 0.02774 0.01837 -0.1135 0.8434 0.0450
-7.250 -0.2607 0.02718 0.01776 -0.1118 0.8389 0.0465
-7.000 -0.2455 0.02665 0.01717 -0.1101 0.8345 0.0483
-6.750 -0.2273 0.02605 0.01650 -0.1089 0.8310 0.0509
-6.500 -0.2072 0.02542 0.01588 -0.1082 0.8281 0.0546
-6.250 -0.1844 0.02480 0.01516 -0.1077 0.8257 0.0596
-6.000 -0.1773 0.02454 0.01496 -0.1047 0.8200 0.0639
-5.750 -0.1618 0.02410 0.01453 -0.1031 0.8161 0.0716
-5.500 -0.1428 0.02356 0.01406 -0.1021 0.8132 0.0859
-5.250 -0.1208 0.02296 0.01358 -0.1016 0.8107 0.1123
-5.000 -0.1006 0.02248 0.01324 -0.1008 0.8079 0.1465
-4.750 -0.0927 0.02237 0.01330 -0.0980 0.8023 0.1796
-4.500 -0.0769 0.02187 0.01312 -0.0967 0.7988 0.2406
-4.250 -0.0600 0.02097 0.01282 -0.0959 0.7959 0.3535
-4.000 -0.0408 0.02053 0.01318 -0.0941 0.7937 0.4979
-3.750 -0.0208 0.02092 0.01369 -0.0921 0.7905 0.5643
-3.500 -0.0098 0.02149 0.01424 -0.0892 0.7852 0.5982
-3.250 0.0120 0.02189 0.01456 -0.0878 0.7818 0.6252
-3.000 0.0388 0.02215 0.01468 -0.0874 0.7793 0.6487
-2.750 0.0673 0.02238 0.01478 -0.0871 0.7773 0.6667
-2.500 0.0956 0.02266 0.01498 -0.0866 0.7757 0.6801
-2.250 0.0949 0.02346 0.01580 -0.0819 0.7681 0.6898
-2.000 0.1172 0.02375 0.01600 -0.0808 0.7647 0.7030
-1.750 0.1427 0.02401 0.01618 -0.0799 0.7623 0.7164
-1.500 0.1686 0.02425 0.01638 -0.0786 0.7604 0.7277
-1.250 0.1730 0.02489 0.01701 -0.0749 0.7538 0.7381
-1.000 0.1894 0.02522 0.01731 -0.0729 0.7492 0.7472
-0.750 0.2164 0.02526 0.01727 -0.0727 0.7465 0.7543
-0.500 0.2465 0.02522 0.01715 -0.0728 0.7444 0.7597
-0.250 0.2618 0.02556 0.01744 -0.0714 0.7391 0.7665
0.000 0.2735 0.02593 0.01781 -0.0690 0.7328 0.7711
0.250 0.3023 0.02588 0.01770 -0.0691 0.7300 0.7752
0.500 0.3366 0.02571 0.01746 -0.0703 0.7280 0.7797
0.750 0.3694 0.02562 0.01729 -0.0715 0.7253 0.7845
1.250 0.3983 0.02613 0.01781 -0.0675 0.7127 0.7922
1.500 0.4371 0.02581 0.01744 -0.0692 0.7108 0.7960
2.000 0.4668 0.02627 0.01791 -0.0656 0.6969 0.8046
2.250 0.5071 0.02580 0.01741 -0.0673 0.6948 0.8078
2.750 0.5435 0.02597 0.01758 -0.0647 0.6803 0.8169
3.000 0.5725 0.02564 0.01726 -0.0645 0.6754 0.8204
3.250 0.5810 0.02598 0.01764 -0.0616 0.6657 0.8253
3.500 0.6233 0.02520 0.01685 -0.0634 0.6628 0.8287
4.000 0.6634 0.02518 0.01688 -0.0611 0.6475 0.8378
4.500 0.7057 0.02511 0.01688 -0.0591 0.6316 0.8481
5.000 0.7484 0.02493 0.01678 -0.0570 0.6149 0.8581
5.250 0.7553 0.02559 0.01751 -0.0545 0.6016 0.8653
5.500 0.7661 0.02600 0.01799 -0.0523 0.5890 0.8719
5.750 0.7871 0.02598 0.01802 -0.0514 0.5780 0.8786
6.000 0.8155 0.02552 0.01759 -0.0511 0.5685 0.8849
6.500 0.8517 0.02570 0.01788 -0.0484 0.5395 0.9031
6.750 0.8751 0.02553 0.01773 -0.0476 0.5241 0.9141
7.250 0.9321 0.02490 0.01706 -0.0475 0.4875 0.9452
7.500 0.9580 0.02485 0.01695 -0.0476 0.4649 1.0000
7.750 0.9851 0.02499 0.01694 -0.0479 0.4422 1.0000
8.000 1.0072 0.02547 0.01730 -0.0477 0.4202 1.0000
8.250 1.0266 0.02612 0.01782 -0.0473 0.3988 1.0000
8.500 1.0446 0.02686 0.01843 -0.0467 0.3793 1.0000
8.750 1.0616 0.02767 0.01914 -0.0461 0.3617 1.0000
9.000 1.0777 0.02854 0.01993 -0.0454 0.3454 1.0000
9.250 1.0930 0.02946 0.02078 -0.0447 0.3303 1.0000
9.500 1.1083 0.03040 0.02168 -0.0439 0.3166 1.0000
9.750 1.1236 0.03136 0.02259 -0.0432 0.3042 1.0000
10.000 1.1387 0.03232 0.02349 -0.0425 0.2929 1.0000
10.250 1.1531 0.03334 0.02449 -0.0417 0.2820 1.0000
10.500 1.1679 0.03436 0.02553 -0.0410 0.2720 1.0000
10.750 1.1819 0.03541 0.02651 -0.0402 0.2629 1.0000
11.000 1.1957 0.03651 0.02769 -0.0395 0.2535 1.0000
11.250 1.2096 0.03760 0.02874 -0.0388 0.2457 1.0000
11.500 1.2225 0.03878 0.02999 -0.0381 0.2372 1.0000
11.750 1.2357 0.03994 0.03114 -0.0374 0.2300 1.0000
12.000 1.2479 0.04121 0.03250 -0.0367 0.2223 1.0000
12.250 1.2605 0.04243 0.03367 -0.0360 0.2159 1.0000
12.500 1.2717 0.04381 0.03519 -0.0354 0.2086 1.0000
12.750 1.2824 0.04520 0.03659 -0.0347 0.2023 1.0000
13.000 1.2932 0.04664 0.03813 -0.0341 0.1959 1.0000
13.250 1.3027 0.04818 0.03974 -0.0334 0.1897 1.0000
13.500 1.3128 0.04969 0.04126 -0.0328 0.1842 1.0000
13.750 1.3212 0.05142 0.04315 -0.0323 0.1781 1.0000
14.000 1.3291 0.05315 0.04492 -0.0318 0.1728 1.0000
14.250 1.3374 0.05493 0.04678 -0.0313 0.1677 1.0000
14.500 1.3433 0.05695 0.04894 -0.0309 0.1621 1.0000
14.750 1.3500 0.05887 0.05088 -0.0305 0.1574 1.0000
15.000 1.3558 0.06102 0.05317 -0.0302 0.1526 1.0000
15.250 1.3597 0.06337 0.05566 -0.0299 0.1476 1.0000
15.500 1.3643 0.06561 0.05792 -0.0297 0.1433 1.0000
15.750 1.3677 0.06813 0.06060 -0.0297 0.1390 1.0000
16.000 1.3693 0.07092 0.06356 -0.0297 0.1345 1.0000
16.250 1.3713 0.07362 0.06632 -0.0298 0.1305 1.0000
16.500 1.3737 0.07636 0.06911 -0.0300 0.1268 1.0000
16.750 1.3715 0.07982 0.07280 -0.0305 0.1227 1.0000
17.000 1.3705 0.08313 0.07623 -0.0311 0.1190 1.0000
17.250 1.3723 0.08602 0.07914 -0.0316 0.1157 1.0000
17.500 1.3680 0.09000 0.08331 -0.0325 0.1122 1.0000
17.750 1.3622 0.09426 0.08778 -0.0337 0.1088 1.0000
18.000 1.3585 0.09823 0.09186 -0.0350 0.1056 1.0000
18.250 1.3600 0.10134 0.09498 -0.0360 0.1027 1.0000
18.500 1.3509 0.10637 0.10022 -0.0379 0.0999 1.0000
18.750 1.3388 0.11204 0.10611 -0.0402 0.0970 1.0000
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Polar data table (+)
Polar graphs
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