EPPLER 1200 AIRFOIL (e1200-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1200 AIRFOIL (e1200-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.38 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1200-il-1000000-n5.txt Download as CSV file: xf-e1200-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.7380 0.09690 0.09424 -0.0755 1.0000 0.0105
-17.750 -0.7735 0.08696 0.08415 -0.0809 1.0000 0.0104
-17.500 -0.8006 0.07872 0.07576 -0.0855 1.0000 0.0105
-17.250 -0.8222 0.07161 0.06853 -0.0894 1.0000 0.0104
-17.000 -0.8315 0.06486 0.06163 -0.0951 0.9991 0.0105
-16.750 -0.8476 0.05864 0.05528 -0.0986 0.9919 0.0105
-16.500 -0.8512 0.05367 0.05018 -0.1026 0.9819 0.0106
-16.250 -0.8340 0.04854 0.04487 -0.1110 0.9552 0.0106
-16.000 -0.8024 0.04379 0.03993 -0.1215 0.9424 0.0107
-15.750 -0.7674 0.03978 0.03571 -0.1314 0.9281 0.0108
-15.500 -0.7377 0.03717 0.03280 -0.1379 0.8914 0.0109
-15.250 -0.7377 0.03513 0.03054 -0.1378 0.8628 0.0109
-15.000 -0.7352 0.03348 0.02874 -0.1373 0.8457 0.0109
-14.750 -0.7331 0.03180 0.02693 -0.1367 0.8332 0.0109
-14.500 -0.7329 0.03004 0.02504 -0.1359 0.8230 0.0111
-14.250 -0.7262 0.02877 0.02367 -0.1352 0.8140 0.0110
-14.000 -0.7266 0.02706 0.02186 -0.1340 0.8059 0.0113
-13.750 -0.7205 0.02582 0.02053 -0.1331 0.7986 0.0114
-13.500 -0.7124 0.02477 0.01939 -0.1320 0.7921 0.0114
-13.250 -0.7026 0.02377 0.01834 -0.1311 0.7869 0.0116
-13.000 -0.6913 0.02292 0.01743 -0.1301 0.7817 0.0117
-12.750 -0.6811 0.02205 0.01648 -0.1289 0.7769 0.0118
-12.500 -0.6683 0.02130 0.01568 -0.1279 0.7730 0.0119
-12.250 -0.6539 0.02066 0.01500 -0.1270 0.7690 0.0121
-12.000 -0.6412 0.01995 0.01422 -0.1258 0.7649 0.0122
-11.750 -0.6287 0.01927 0.01348 -0.1245 0.7609 0.0124
-11.500 -0.6158 0.01861 0.01276 -0.1232 0.7574 0.0125
-11.250 -0.6019 0.01800 0.01211 -0.1219 0.7541 0.0127
-11.000 -0.5895 0.01738 0.01143 -0.1203 0.7508 0.0128
-10.750 -0.5771 0.01683 0.01083 -0.1185 0.7476 0.0129
-10.500 -0.5663 0.01639 0.01033 -0.1163 0.7446 0.0130
-10.250 -0.5510 0.01602 0.00990 -0.1147 0.7420 0.0133
-10.000 -0.5327 0.01558 0.00943 -0.1136 0.7398 0.0134
-9.750 -0.5133 0.01518 0.00898 -0.1126 0.7373 0.0136
-9.500 -0.4926 0.01482 0.00858 -0.1118 0.7346 0.0137
-9.250 -0.4710 0.01449 0.00821 -0.1111 0.7321 0.0138
-9.000 -0.4512 0.01401 0.00768 -0.1102 0.7297 0.0141
-8.750 -0.4299 0.01362 0.00725 -0.1095 0.7275 0.0144
-8.500 -0.4070 0.01327 0.00688 -0.1090 0.7256 0.0147
-8.250 -0.3832 0.01295 0.00654 -0.1086 0.7239 0.0150
-8.000 -0.3587 0.01267 0.00625 -0.1083 0.7219 0.0154
-7.750 -0.3341 0.01238 0.00594 -0.1080 0.7197 0.0157
-7.500 -0.3091 0.01212 0.00566 -0.1077 0.7175 0.0161
-7.250 -0.2838 0.01188 0.00538 -0.1075 0.7155 0.0164
-7.000 -0.2581 0.01165 0.00513 -0.1073 0.7137 0.0168
-6.750 -0.2321 0.01145 0.00490 -0.1072 0.7118 0.0171
-6.250 -0.1803 0.01093 0.00436 -0.1069 0.7083 0.0186
-6.000 -0.1535 0.01072 0.00414 -0.1069 0.7066 0.0193
-5.750 -0.1265 0.01052 0.00394 -0.1070 0.7047 0.0200
-5.500 -0.0993 0.01034 0.00375 -0.1070 0.7030 0.0207
-5.250 -0.0720 0.01016 0.00356 -0.1071 0.7012 0.0218
-5.000 -0.0448 0.00998 0.00338 -0.1071 0.6994 0.0235
-4.750 -0.0173 0.00981 0.00321 -0.1072 0.6975 0.0259
-4.500 0.0099 0.00962 0.00304 -0.1073 0.6955 0.0327
-4.000 0.0646 0.00915 0.00273 -0.1076 0.6923 0.0671
-3.750 0.0924 0.00894 0.00260 -0.1078 0.6907 0.0852
-3.500 0.1204 0.00873 0.00248 -0.1081 0.6889 0.1076
-3.250 0.1482 0.00848 0.00236 -0.1083 0.6869 0.1405
-3.000 0.1761 0.00824 0.00224 -0.1086 0.6851 0.1769
-2.750 0.2041 0.00799 0.00213 -0.1090 0.6831 0.2198
-2.500 0.2322 0.00773 0.00203 -0.1093 0.6811 0.2688
-2.250 0.2601 0.00742 0.00191 -0.1097 0.6791 0.3322
-2.000 0.2881 0.00699 0.00178 -0.1102 0.6771 0.4250
-1.750 0.3164 0.00656 0.00171 -0.1108 0.6751 0.5337
-1.500 0.3455 0.00645 0.00172 -0.1111 0.6722 0.5727
-1.250 0.3746 0.00643 0.00171 -0.1114 0.6682 0.5879
-1.000 0.4033 0.00644 0.00169 -0.1116 0.6637 0.5991
-0.750 0.4321 0.00644 0.00170 -0.1118 0.6591 0.6091
-0.500 0.4611 0.00645 0.00170 -0.1121 0.6529 0.6184
-0.250 0.4891 0.00648 0.00171 -0.1121 0.6464 0.6283
0.000 0.5180 0.00650 0.00174 -0.1124 0.6407 0.6375
0.250 0.5466 0.00653 0.00177 -0.1125 0.6346 0.6459
0.500 0.5748 0.00659 0.00179 -0.1127 0.6293 0.6517
0.750 0.6036 0.00661 0.00183 -0.1129 0.6235 0.6560
1.000 0.6315 0.00666 0.00185 -0.1130 0.6166 0.6590
1.250 0.6598 0.00671 0.00188 -0.1131 0.6098 0.6616
1.500 0.6872 0.00678 0.00191 -0.1131 0.6005 0.6640
1.750 0.7149 0.00686 0.00195 -0.1131 0.5909 0.6660
2.000 0.7414 0.00695 0.00201 -0.1130 0.5790 0.6683
2.250 0.7672 0.00707 0.00208 -0.1126 0.5640 0.6706
2.500 0.7919 0.00724 0.00218 -0.1121 0.5447 0.6729
2.750 0.8151 0.00747 0.00231 -0.1113 0.5218 0.6751
3.000 0.8361 0.00779 0.00249 -0.1101 0.4915 0.6774
3.250 0.8561 0.00814 0.00271 -0.1088 0.4610 0.6799
3.500 0.8765 0.00848 0.00291 -0.1075 0.4351 0.6821
4.000 0.9148 0.00917 0.00338 -0.1045 0.3834 0.6862
4.250 0.9337 0.00949 0.00361 -0.1030 0.3623 0.6884
4.500 0.9515 0.00981 0.00385 -0.1013 0.3427 0.6909
4.750 0.9672 0.01011 0.00407 -0.0991 0.3242 0.6935
5.000 0.9829 0.01041 0.00431 -0.0970 0.3087 0.6961
5.250 0.9990 0.01075 0.00458 -0.0950 0.2936 0.6983
5.750 1.0324 0.01142 0.00515 -0.0913 0.2677 0.7027
6.000 1.0494 0.01174 0.00546 -0.0895 0.2576 0.7054
6.250 1.0652 0.01213 0.00580 -0.0877 0.2464 0.7082
6.500 1.0827 0.01246 0.00612 -0.0861 0.2378 0.7109
6.750 1.0988 0.01286 0.00649 -0.0844 0.2291 0.7135
7.000 1.1150 0.01327 0.00687 -0.0827 0.2202 0.7160
7.250 1.1313 0.01369 0.00728 -0.0811 0.2129 0.7185
7.500 1.1479 0.01410 0.00770 -0.0796 0.2062 0.7215
7.750 1.1636 0.01457 0.00817 -0.0781 0.1999 0.7247
8.000 1.1804 0.01503 0.00863 -0.0767 0.1937 0.7279
8.250 1.1951 0.01559 0.00917 -0.0751 0.1867 0.7310
8.500 1.2119 0.01608 0.00967 -0.0738 0.1814 0.7339
8.750 1.2272 0.01665 0.01024 -0.0724 0.1751 0.7369
9.000 1.2422 0.01724 0.01084 -0.0710 0.1692 0.7406
9.250 1.2586 0.01779 0.01142 -0.0698 0.1647 0.7446
9.500 1.2731 0.01846 0.01208 -0.0684 0.1588 0.7486
10.000 1.3038 0.01976 0.01341 -0.0660 0.1487 0.7564
10.250 1.3176 0.02051 0.01416 -0.0646 0.1434 0.7609
10.500 1.3327 0.02120 0.01489 -0.0635 0.1389 0.7655
10.750 1.3450 0.02208 0.01574 -0.0621 0.1310 0.7701
11.000 1.3596 0.02283 0.01653 -0.0610 0.1278 0.7759
11.250 1.3735 0.02363 0.01735 -0.0599 0.1222 0.7820
11.500 1.3843 0.02465 0.01835 -0.0585 0.1147 0.7883
11.750 1.3987 0.02545 0.01921 -0.0574 0.1111 0.7957
12.000 1.4109 0.02641 0.02018 -0.0563 0.1058 0.8029
12.250 1.4223 0.02743 0.02122 -0.0551 0.1002 0.8117
12.500 1.4322 0.02857 0.02236 -0.0538 0.0927 0.8213
12.750 1.4438 0.02962 0.02345 -0.0527 0.0886 0.8333
13.000 1.4557 0.03062 0.02452 -0.0516 0.0844 0.8491
13.250 1.4639 0.03183 0.02579 -0.0501 0.0793 0.8742
13.750 1.4849 0.03413 0.02826 -0.0483 0.0703 1.0000
14.250 1.5075 0.03667 0.03084 -0.0467 0.0639 1.0000
14.500 1.5152 0.03826 0.03243 -0.0459 0.0595 1.0000
14.750 1.5258 0.03964 0.03382 -0.0452 0.0566 1.0000
15.000 1.5338 0.04128 0.03548 -0.0444 0.0527 1.0000
15.250 1.5416 0.04297 0.03717 -0.0438 0.0495 1.0000
15.500 1.5504 0.04460 0.03883 -0.0432 0.0468 1.0000
15.750 1.5563 0.04653 0.04077 -0.0426 0.0431 1.0000
16.000 1.5634 0.04839 0.04266 -0.0421 0.0407 1.0000
16.250 1.5709 0.05025 0.04455 -0.0417 0.0384 1.0000
16.500 1.5744 0.05256 0.04688 -0.0412 0.0354 1.0000
16.750 1.5804 0.05466 0.04901 -0.0409 0.0329 1.0000
17.000 1.5829 0.05718 0.05156 -0.0406 0.0301 1.0000
17.250 1.5865 0.05962 0.05404 -0.0405 0.0279 1.0000
17.500 1.5867 0.06251 0.05696 -0.0404 0.0249 1.0000
17.750 1.5895 0.06519 0.05970 -0.0405 0.0235 1.0000
18.000 1.5891 0.06830 0.06285 -0.0406 0.0211 1.0000
18.250 1.5894 0.07139 0.06599 -0.0409 0.0196 1.0000
18.500 1.5872 0.07488 0.06953 -0.0414 0.0175 1.0000
18.750 1.5832 0.07870 0.07341 -0.0420 0.0155 1.0000
19.000 1.5776 0.08284 0.07762 -0.0429 0.0135 1.0000
19.250 1.5731 0.08691 0.08176 -0.0439 0.0118 1.0000
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