EPPLER E1212MOD AIRFOIL (e1212mod-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E1212MOD AIRFOIL (e1212mod-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.39 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1212mod-il-1000000.txt Download as CSV file: xf-e1212mod-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E1212MOD 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.8610 0.08905 0.08557 -0.0298 1.0000 0.0180
-15.250 -0.8832 0.08225 0.07869 -0.0335 1.0000 0.0182
-15.000 -0.9017 0.07614 0.07251 -0.0368 1.0000 0.0180
-14.750 -0.9338 0.06846 0.06471 -0.0412 1.0000 0.0179
-14.500 -0.9704 0.06035 0.05646 -0.0460 1.0000 0.0178
-14.250 -1.0380 0.04816 0.04405 -0.0537 1.0000 0.0178
-14.000 -1.0738 0.03894 0.03463 -0.0604 1.0000 0.0176
-13.750 -1.0974 0.03020 0.02563 -0.0694 1.0000 0.0176
-13.500 -1.1089 0.02675 0.02202 -0.0709 1.0000 0.0176
-13.250 -1.1152 0.02494 0.02012 -0.0689 1.0000 0.0177
-13.000 -1.1181 0.02378 0.01889 -0.0656 1.0000 0.0177
-12.750 -1.1134 0.02267 0.01771 -0.0631 1.0000 0.0178
-12.500 -1.1035 0.02173 0.01671 -0.0611 1.0000 0.0179
-12.250 -1.0913 0.02088 0.01581 -0.0592 1.0000 0.0180
-12.000 -1.0775 0.02009 0.01496 -0.0574 1.0000 0.0182
-11.750 -1.0586 0.01930 0.01413 -0.0565 0.9899 0.0183
-11.500 -0.9964 0.01817 0.01292 -0.0643 0.9482 0.0187
-11.250 -0.9572 0.01761 0.01200 -0.0670 0.8397 0.0190
-11.000 -0.9390 0.01722 0.01145 -0.0654 0.8077 0.0191
-10.750 -0.9186 0.01679 0.01091 -0.0641 0.7904 0.0192
-10.500 -0.8974 0.01636 0.01038 -0.0630 0.7773 0.0194
-10.250 -0.8751 0.01596 0.00990 -0.0621 0.7660 0.0196
-10.000 -0.8524 0.01556 0.00941 -0.0611 0.7557 0.0199
-9.750 -0.8296 0.01511 0.00890 -0.0602 0.7454 0.0204
-9.500 -0.8062 0.01472 0.00845 -0.0594 0.7362 0.0209
-9.250 -0.7821 0.01432 0.00800 -0.0586 0.7263 0.0215
-9.000 -0.7580 0.01397 0.00758 -0.0578 0.7154 0.0224
-8.750 -0.7344 0.01348 0.00708 -0.0570 0.7028 0.0254
-8.500 -0.7136 0.01271 0.00639 -0.0559 0.6890 0.0452
-8.250 -0.6891 0.01234 0.00600 -0.0551 0.6703 0.0522
-8.000 -0.6645 0.01200 0.00561 -0.0544 0.6438 0.0594
-7.750 -0.6406 0.01165 0.00520 -0.0536 0.6089 0.0686
-7.500 -0.6168 0.01130 0.00481 -0.0527 0.5768 0.0817
-7.250 -0.5920 0.01097 0.00451 -0.0521 0.5572 0.0977
-7.000 -0.5655 0.01080 0.00434 -0.0516 0.5437 0.1092
-6.750 -0.5382 0.01069 0.00422 -0.0512 0.5334 0.1164
-6.500 -0.5103 0.01062 0.00411 -0.0509 0.5251 0.1216
-6.250 -0.4823 0.01053 0.00400 -0.0506 0.5195 0.1254
-6.000 -0.4543 0.01045 0.00391 -0.0503 0.5134 0.1292
-5.750 -0.4262 0.01042 0.00384 -0.0500 0.5066 0.1323
-5.500 -0.3974 0.01038 0.00376 -0.0498 0.5029 0.1344
-5.250 -0.3694 0.01024 0.00364 -0.0495 0.4991 0.1381
-5.000 -0.3411 0.01018 0.00357 -0.0492 0.4945 0.1411
-4.750 -0.3126 0.01016 0.00351 -0.0489 0.4893 0.1437
-4.500 -0.2842 0.01017 0.00346 -0.0487 0.4833 0.1454
-4.250 -0.2555 0.01007 0.00335 -0.0484 0.4802 0.1474
-4.000 -0.2274 0.00993 0.00323 -0.0481 0.4764 0.1509
-3.750 -0.1990 0.00986 0.00315 -0.0479 0.4721 0.1535
-3.500 -0.1705 0.00982 0.00308 -0.0476 0.4673 0.1557
-3.250 -0.1422 0.00982 0.00304 -0.0473 0.4617 0.1577
-3.000 -0.1129 0.00978 0.00299 -0.0472 0.4589 0.1594
-2.750 -0.0847 0.00962 0.00285 -0.0469 0.4553 0.1635
-2.500 -0.0563 0.00953 0.00277 -0.0467 0.4508 0.1667
-2.250 -0.0279 0.00949 0.00270 -0.0464 0.4458 0.1694
-2.000 0.0005 0.00948 0.00265 -0.0461 0.4404 0.1717
-1.750 0.0297 0.00941 0.00259 -0.0460 0.4367 0.1736
-1.500 0.0583 0.00933 0.00250 -0.0457 0.4312 0.1760
-1.250 0.0864 0.00925 0.00240 -0.0454 0.4246 0.1798
-1.000 0.1149 0.00920 0.00235 -0.0452 0.4184 0.1833
-0.750 0.1436 0.00914 0.00229 -0.0449 0.4112 0.1867
-0.500 0.1720 0.00915 0.00224 -0.0447 0.4027 0.1895
-0.250 0.2002 0.00907 0.00219 -0.0444 0.3954 0.1970
0.000 0.2283 0.00905 0.00216 -0.0441 0.3864 0.2045
0.250 0.2562 0.00900 0.00214 -0.0438 0.3784 0.2178
0.500 0.2839 0.00896 0.00214 -0.0435 0.3700 0.2379
0.750 0.3116 0.00896 0.00218 -0.0431 0.3619 0.2605
1.000 0.3400 0.00899 0.00222 -0.0429 0.3550 0.2755
1.250 0.3677 0.00904 0.00227 -0.0426 0.3470 0.2869
1.500 0.3962 0.00910 0.00232 -0.0423 0.3413 0.2942
1.750 0.4243 0.00913 0.00235 -0.0420 0.3352 0.3021
2.000 0.4519 0.00922 0.00242 -0.0417 0.3282 0.3091
2.250 0.4804 0.00928 0.00247 -0.0415 0.3236 0.3143
2.500 0.5083 0.00931 0.00251 -0.0412 0.3183 0.3220
2.750 0.5359 0.00939 0.00258 -0.0408 0.3123 0.3289
3.000 0.5637 0.00948 0.00266 -0.0405 0.3072 0.3345
3.250 0.5918 0.00951 0.00271 -0.0402 0.3032 0.3427
3.500 0.6194 0.00957 0.00279 -0.0399 0.2986 0.3515
3.750 0.6465 0.00967 0.00289 -0.0395 0.2934 0.3622
4.000 0.6740 0.00973 0.00299 -0.0391 0.2896 0.3776
4.250 0.7016 0.00973 0.00308 -0.0388 0.2865 0.4022
4.500 0.7285 0.00975 0.00318 -0.0384 0.2828 0.4354
4.750 0.7550 0.00979 0.00329 -0.0379 0.2789 0.4703
5.000 0.7797 0.00978 0.00346 -0.0372 0.2743 0.5405
5.250 0.8029 0.00951 0.00361 -0.0361 0.2722 0.6867
5.500 0.8275 0.00941 0.00372 -0.0352 0.2698 0.7555
5.750 0.8675 0.00912 0.00395 -0.0372 0.2661 0.9569
6.000 0.9286 0.00937 0.00414 -0.0439 0.2613 0.9917
6.250 0.9682 0.00962 0.00435 -0.0462 0.2568 1.0000
6.500 0.9931 0.00973 0.00446 -0.0453 0.2555 1.0000
6.750 1.0178 0.00986 0.00459 -0.0445 0.2538 1.0000
7.000 1.0423 0.01000 0.00473 -0.0436 0.2518 1.0000
7.250 1.0667 0.01016 0.00488 -0.0427 0.2496 1.0000
7.500 1.0908 0.01034 0.00504 -0.0418 0.2475 1.0000
7.750 1.1144 0.01055 0.00523 -0.0408 0.2452 1.0000
8.000 1.1371 0.01081 0.00546 -0.0397 0.2422 1.0000
8.250 1.1612 0.01099 0.00565 -0.0388 0.2403 1.0000
8.500 1.1862 0.01112 0.00579 -0.0381 0.2389 1.0000
8.750 1.2109 0.01126 0.00595 -0.0373 0.2371 1.0000
9.000 1.2351 0.01143 0.00612 -0.0364 0.2353 1.0000
9.250 1.2589 0.01162 0.00632 -0.0355 0.2335 1.0000
9.500 1.2822 0.01183 0.00653 -0.0346 0.2315 1.0000
9.750 1.3048 0.01208 0.00676 -0.0336 0.2294 1.0000
10.000 1.3258 0.01239 0.00706 -0.0323 0.2264 1.0000
10.250 1.3490 0.01259 0.00728 -0.0314 0.2247 1.0000
10.500 1.3729 0.01275 0.00747 -0.0305 0.2235 1.0000
10.750 1.3961 0.01294 0.00769 -0.0296 0.2221 1.0000
11.000 1.4190 0.01313 0.00791 -0.0287 0.2203 1.0000
11.250 1.4408 0.01336 0.00815 -0.0276 0.2182 1.0000
11.500 1.4615 0.01362 0.00841 -0.0263 0.2159 1.0000
11.750 1.4805 0.01394 0.00873 -0.0248 0.2136 1.0000
12.000 1.4955 0.01433 0.00912 -0.0227 0.2108 1.0000
12.250 1.5148 0.01452 0.00935 -0.0212 0.2092 1.0000
12.500 1.5335 0.01473 0.00960 -0.0196 0.2074 1.0000
12.750 1.5510 0.01499 0.00990 -0.0179 0.2050 1.0000
13.000 1.5667 0.01534 0.01027 -0.0161 0.2024 1.0000
13.250 1.5809 0.01578 0.01071 -0.0142 0.1995 1.0000
13.500 1.5926 0.01636 0.01130 -0.0121 0.1961 1.0000
13.750 1.6113 0.01670 0.01169 -0.0110 0.1938 1.0000
14.000 1.6275 0.01718 0.01220 -0.0097 0.1900 1.0000
14.250 1.6375 0.01802 0.01302 -0.0080 0.1836 1.0000
14.500 1.6515 0.01875 0.01377 -0.0069 0.1774 1.0000
14.750 1.6590 0.02000 0.01499 -0.0057 0.1684 1.0000
15.000 1.6633 0.02165 0.01661 -0.0048 0.1567 1.0000
15.250 1.6544 0.02456 0.01943 -0.0040 0.1397 1.0000
15.500 1.6482 0.02738 0.02225 -0.0035 0.1309 1.0000
15.750 1.6403 0.03048 0.02536 -0.0032 0.1247 1.0000
16.000 1.6386 0.03309 0.02803 -0.0031 0.1214 1.0000
16.250 1.6315 0.03634 0.03133 -0.0032 0.1182 1.0000
16.500 1.6214 0.04002 0.03506 -0.0035 0.1153 1.0000
16.750 1.6154 0.04335 0.03848 -0.0039 0.1135 1.0000
17.000 1.6083 0.04681 0.04200 -0.0043 0.1116 1.0000
17.250 1.5992 0.05057 0.04584 -0.0049 0.1101 1.0000
17.500 1.5865 0.05476 0.05010 -0.0056 0.1085 1.0000
17.750 1.5708 0.05935 0.05477 -0.0065 0.1069 1.0000
18.000 1.5532 0.06421 0.05970 -0.0075 0.1052 1.0000
18.250 1.5435 0.06821 0.06377 -0.0083 0.1040 1.0000
18.500 1.5371 0.07191 0.06756 -0.0090 0.1030 1.0000
18.750 1.5282 0.07594 0.07167 -0.0099 0.1020 1.0000
19.000 1.5196 0.07996 0.07576 -0.0109 0.1008 1.0000
19.250 1.5069 0.08457 0.08043 -0.0120 0.0996 1.0000
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