EPPLER 1200 AIRFOIL (e1200-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1200 AIRFOIL (e1200-il) Reynolds number: 200,000 Max Cl/Cd: 69.51 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1200-il-200000.txt Download as CSV file: xf-e1200-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.0896 0.10400 0.10050 -0.0976 0.9484 0.0765
-12.000 -0.1263 0.09601 0.09254 -0.1065 0.9455 0.0813
-11.750 -0.1171 0.09015 0.08667 -0.1086 0.9428 0.0825
-11.500 -0.0923 0.08751 0.08399 -0.1093 0.9390 0.0837
-11.250 -0.0771 0.08458 0.08103 -0.1103 0.9333 0.0854
-11.000 -0.0684 0.08049 0.07692 -0.1128 0.9290 0.0875
-10.750 -0.0703 0.07483 0.07124 -0.1168 0.9254 0.0908
-10.500 -0.3871 0.04859 0.04377 -0.1358 0.9195 0.0495
-10.250 -0.3857 0.04479 0.03985 -0.1355 0.9122 0.0480
-10.000 -0.4361 0.03898 0.03307 -0.1295 0.8997 0.0432
-9.500 -0.4165 0.03523 0.02870 -0.1266 0.8894 0.0422
-9.250 -0.4064 0.03330 0.02653 -0.1248 0.8837 0.0422
-9.000 -0.3902 0.03138 0.02434 -0.1239 0.8794 0.0422
-8.750 -0.3701 0.02978 0.02244 -0.1233 0.8762 0.0423
-8.500 -0.3540 0.02803 0.02056 -0.1220 0.8716 0.0431
-8.250 -0.3332 0.02686 0.01937 -0.1214 0.8676 0.0442
-8.000 -0.3108 0.02597 0.01841 -0.1209 0.8643 0.0455
-7.750 -0.2856 0.02494 0.01727 -0.1207 0.8615 0.0464
-7.500 -0.2593 0.02399 0.01620 -0.1205 0.8589 0.0475
-7.250 -0.2416 0.02341 0.01557 -0.1190 0.8544 0.0485
-7.000 -0.2207 0.02286 0.01494 -0.1179 0.8508 0.0498
-6.750 -0.1990 0.02196 0.01407 -0.1171 0.8478 0.0515
-6.500 -0.1769 0.02138 0.01353 -0.1165 0.8451 0.0545
-6.250 -0.1531 0.02090 0.01299 -0.1160 0.8428 0.0578
-6.000 -0.1416 0.02056 0.01268 -0.1136 0.8382 0.0606
-5.750 -0.1267 0.02019 0.01237 -0.1119 0.8343 0.0651
-5.500 -0.1088 0.01970 0.01189 -0.1107 0.8311 0.0729
-5.250 -0.0890 0.01897 0.01131 -0.1098 0.8284 0.0972
-5.000 -0.0690 0.01802 0.01076 -0.1093 0.8261 0.1698
-4.750 -0.0600 0.01786 0.01090 -0.1069 0.8213 0.2251
-4.500 -0.0453 0.01747 0.01086 -0.1056 0.8173 0.3035
-4.250 -0.0261 0.01670 0.01072 -0.1050 0.8143 0.4365
-4.000 -0.0018 0.01658 0.01109 -0.1041 0.8120 0.5613
-3.750 0.0272 0.01691 0.01143 -0.1037 0.8102 0.6172
-3.500 0.0459 0.01766 0.01220 -0.1017 0.8068 0.6450
-3.250 0.0569 0.01848 0.01303 -0.0987 0.8012 0.6627
-3.000 0.0809 0.01897 0.01348 -0.0975 0.7982 0.6782
-2.750 0.1082 0.01933 0.01381 -0.0967 0.7961 0.6907
-2.500 0.1379 0.01960 0.01400 -0.0965 0.7943 0.7036
-2.250 0.1679 0.01987 0.01421 -0.0962 0.7927 0.7140
-2.000 0.1611 0.02094 0.01534 -0.0908 0.7840 0.7213
-1.750 0.1860 0.02121 0.01557 -0.0899 0.7811 0.7302
-1.500 0.2160 0.02129 0.01561 -0.0897 0.7791 0.7387
-1.250 0.2475 0.02139 0.01565 -0.0897 0.7775 0.7488
-1.000 0.2427 0.02239 0.01671 -0.0843 0.7694 0.7562
-0.750 0.2639 0.02268 0.01696 -0.0830 0.7652 0.7670
-0.500 0.2919 0.02265 0.01693 -0.0821 0.7630 0.7737
-0.250 0.3276 0.02245 0.01667 -0.0831 0.7614 0.7803
0.000 0.3663 0.02215 0.01629 -0.0849 0.7600 0.7861
0.250 0.3524 0.02320 0.01742 -0.0783 0.7489 0.7911
0.500 0.3899 0.02285 0.01702 -0.0798 0.7468 0.7957
0.750 0.4337 0.02238 0.01646 -0.0826 0.7453 0.8003
1.000 0.4738 0.02187 0.01590 -0.0843 0.7437 0.8033
1.250 0.4687 0.02264 0.01675 -0.0792 0.7331 0.8077
1.500 0.5111 0.02201 0.01607 -0.0813 0.7307 0.8110
1.750 0.5579 0.02124 0.01523 -0.0842 0.7286 0.8145
2.000 0.6059 0.02053 0.01443 -0.0875 0.7266 0.8176
2.250 0.6074 0.02096 0.01495 -0.0832 0.7167 0.8213
2.500 0.6464 0.02036 0.01432 -0.0847 0.7135 0.8245
2.750 0.6891 0.01974 0.01365 -0.0870 0.7111 0.8275
3.000 0.7041 0.01996 0.01393 -0.0853 0.7028 0.8319
3.250 0.7385 0.01952 0.01348 -0.0863 0.6983 0.8352
3.500 0.7777 0.01892 0.01285 -0.0878 0.6952 0.8380
3.750 0.7940 0.01897 0.01297 -0.0859 0.6873 0.8420
4.000 0.8275 0.01854 0.01254 -0.0867 0.6819 0.8455
4.250 0.8711 0.01793 0.01187 -0.0893 0.6781 0.8490
4.500 0.8823 0.01795 0.01200 -0.0864 0.6685 0.8532
4.750 0.9187 0.01737 0.01140 -0.0875 0.6631 0.8565
5.000 0.9365 0.01726 0.01136 -0.0858 0.6535 0.8611
5.250 0.9740 0.01673 0.01080 -0.0873 0.6467 0.8649
5.500 0.9866 0.01659 0.01076 -0.0845 0.6354 0.8696
5.750 1.0079 0.01630 0.01051 -0.0831 0.6248 0.8746
6.000 1.0342 0.01598 0.01019 -0.0827 0.6132 0.8796
6.250 1.0530 0.01575 0.00997 -0.0809 0.5989 0.8845
6.500 1.0639 0.01564 0.00990 -0.0777 0.5817 0.8907
6.750 1.0746 0.01562 0.00987 -0.0746 0.5618 0.8982
7.000 1.0850 0.01561 0.00981 -0.0712 0.5390 0.9059
7.250 1.0953 0.01582 0.00991 -0.0682 0.5121 0.9146
7.500 1.1025 0.01616 0.01011 -0.0648 0.4839 0.9251
7.750 1.1069 0.01665 0.01044 -0.0611 0.4563 0.9394
8.000 1.1154 0.01731 0.01101 -0.0587 0.4282 0.9632
8.250 1.1293 0.01819 0.01173 -0.0579 0.4015 1.0000
8.500 1.1423 0.01922 0.01261 -0.0571 0.3787 1.0000
8.750 1.1557 0.02027 0.01350 -0.0562 0.3593 1.0000
9.000 1.1691 0.02130 0.01444 -0.0554 0.3416 1.0000
9.250 1.1824 0.02233 0.01537 -0.0545 0.3262 1.0000
9.500 1.1958 0.02335 0.01630 -0.0535 0.3124 1.0000
9.750 1.2093 0.02434 0.01725 -0.0526 0.2994 1.0000
10.000 1.2235 0.02531 0.01820 -0.0517 0.2881 1.0000
10.250 1.2375 0.02632 0.01910 -0.0508 0.2780 1.0000
10.500 1.2509 0.02730 0.02010 -0.0498 0.2678 1.0000
10.750 1.2648 0.02830 0.02107 -0.0489 0.2587 1.0000
11.000 1.2782 0.02932 0.02206 -0.0479 0.2499 1.0000
11.250 1.2919 0.03034 0.02310 -0.0470 0.2416 1.0000
11.500 1.3051 0.03139 0.02410 -0.0461 0.2336 1.0000
11.750 1.3183 0.03246 0.02523 -0.0452 0.2260 1.0000
12.000 1.3307 0.03357 0.02631 -0.0443 0.2188 1.0000
12.250 1.3438 0.03469 0.02747 -0.0435 0.2117 1.0000
12.500 1.3549 0.03588 0.02871 -0.0426 0.2049 1.0000
12.750 1.3683 0.03703 0.02983 -0.0418 0.1984 1.0000
13.000 1.3778 0.03835 0.03125 -0.0409 0.1919 1.0000
13.250 1.3928 0.03946 0.03224 -0.0403 0.1855 1.0000
13.500 1.3997 0.04099 0.03397 -0.0393 0.1797 1.0000
13.750 1.4090 0.04242 0.03542 -0.0385 0.1741 1.0000
14.000 1.4204 0.04379 0.03679 -0.0378 0.1684 1.0000
14.250 1.4270 0.04546 0.03859 -0.0370 0.1628 1.0000
14.500 1.4372 0.04692 0.04000 -0.0364 0.1575 1.0000
14.750 1.4443 0.04870 0.04191 -0.0357 0.1523 1.0000
15.000 1.4499 0.05056 0.04387 -0.0351 0.1472 1.0000
15.250 1.4622 0.05196 0.04514 -0.0346 0.1420 1.0000
15.500 1.4638 0.05429 0.04770 -0.0340 0.1377 1.0000
15.750 1.4682 0.05640 0.04990 -0.0336 0.1331 1.0000
16.000 1.4795 0.05794 0.05133 -0.0332 0.1283 1.0000
16.250 1.4797 0.06059 0.05421 -0.0329 0.1245 1.0000
16.500 1.4821 0.06307 0.05681 -0.0327 0.1203 1.0000
16.750 1.4876 0.06522 0.05892 -0.0326 0.1161 1.0000
17.000 1.4895 0.06791 0.06175 -0.0325 0.1123 1.0000
17.250 1.4891 0.07090 0.06488 -0.0327 0.1085 1.0000
17.500 1.4895 0.07380 0.06781 -0.0329 0.1047 1.0000
17.750 1.4933 0.07635 0.07038 -0.0331 0.1010 1.0000
18.000 1.4893 0.08002 0.07426 -0.0337 0.0976 1.0000
18.250 1.4874 0.08347 0.07781 -0.0344 0.0943 1.0000
18.500 1.4895 0.08630 0.08060 -0.0350 0.0908 1.0000
18.750 1.4849 0.09029 0.08476 -0.0360 0.0878 1.0000
19.000 1.4796 0.09446 0.08911 -0.0372 0.0849 1.0000
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