EPPLER E1212MOD AIRFOIL (e1212mod-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E1212MOD AIRFOIL (e1212mod-il) Reynolds number: 100,000 Max Cl/Cd: 27.95 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1212mod-il-100000.txt Download as CSV file: xf-e1212mod-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3866 0.08046 0.07570 -0.0349 1.0000 0.2060
-8.000 -0.3729 0.07768 0.07300 -0.0339 1.0000 0.2067
-7.750 -0.3667 0.07607 0.07154 -0.0321 1.0000 0.2077
-7.500 -0.3616 0.06561 0.06099 -0.0458 0.9513 0.2018
-7.250 -0.4728 0.04036 0.03442 -0.0666 0.9087 0.2066
-7.000 -0.4141 0.04239 0.03675 -0.0673 0.8805 0.2108
-6.750 -0.3957 0.04088 0.03501 -0.0670 0.8521 0.2162
-6.500 -0.4065 0.03615 0.02942 -0.0662 0.8295 0.2228
-6.250 -0.3752 0.03656 0.03000 -0.0652 0.8070 0.2265
-6.000 -0.3509 0.03658 0.02996 -0.0639 0.7870 0.2313
-5.750 -0.3399 0.03468 0.02764 -0.0629 0.7707 0.2373
-5.500 -0.3232 0.03337 0.02603 -0.0617 0.7565 0.2421
-5.250 -0.2966 0.03350 0.02623 -0.0607 0.7415 0.2464
-5.000 -0.2760 0.03275 0.02532 -0.0598 0.7281 0.2515
-4.750 -0.2590 0.03132 0.02339 -0.0588 0.7179 0.2565
-4.500 -0.2366 0.03045 0.02248 -0.0581 0.7053 0.2602
-4.250 -0.2115 0.03004 0.02199 -0.0572 0.6957 0.2638
-4.000 -0.1881 0.02939 0.02125 -0.0566 0.6837 0.2677
-3.750 -0.1649 0.02857 0.02011 -0.0558 0.6754 0.2722
-3.500 -0.1424 0.02778 0.01904 -0.0552 0.6640 0.2762
-3.250 -0.1168 0.02707 0.01828 -0.0545 0.6555 0.2795
-3.000 -0.0917 0.02668 0.01789 -0.0539 0.6446 0.2836
-2.750 -0.0660 0.02616 0.01719 -0.0532 0.6359 0.2884
-2.500 -0.0411 0.02569 0.01650 -0.0526 0.6259 0.2933
-2.250 -0.0152 0.02507 0.01576 -0.0520 0.6167 0.2976
-2.000 0.0108 0.02475 0.01542 -0.0514 0.6075 0.3027
-1.750 0.0368 0.02442 0.01499 -0.0507 0.5974 0.3092
-1.500 0.0634 0.02407 0.01438 -0.0501 0.5891 0.3160
-1.250 0.0890 0.02374 0.01416 -0.0495 0.5785 0.3221
-1.000 0.1166 0.02347 0.01369 -0.0489 0.5707 0.3309
-0.750 0.1414 0.02327 0.01355 -0.0483 0.5597 0.3398
-0.500 0.1685 0.02307 0.01327 -0.0477 0.5514 0.3511
-0.250 0.1937 0.02297 0.01322 -0.0470 0.5417 0.3631
0.000 0.2200 0.02288 0.01304 -0.0464 0.5327 0.3786
0.250 0.2464 0.02281 0.01300 -0.0457 0.5251 0.3946
0.500 0.2705 0.02281 0.01316 -0.0450 0.5152 0.4125
0.750 0.2973 0.02273 0.01303 -0.0443 0.5079 0.4329
1.000 0.3215 0.02284 0.01325 -0.0435 0.4992 0.4531
1.250 0.3465 0.02282 0.01332 -0.0428 0.4906 0.4741
1.500 0.3740 0.02281 0.01326 -0.0422 0.4844 0.4974
1.750 0.3964 0.02301 0.01372 -0.0413 0.4757 0.5213
2.000 0.4216 0.02307 0.01390 -0.0405 0.4685 0.5510
2.250 0.4493 0.02304 0.01394 -0.0399 0.4631 0.5917
2.500 0.4699 0.02319 0.01461 -0.0385 0.4557 0.6497
2.750 0.4963 0.02295 0.01499 -0.0372 0.4487 0.7985
3.000 0.6034 0.02311 0.01504 -0.0512 0.4394 1.0000
3.250 0.6199 0.02376 0.01571 -0.0497 0.4324 1.0000
3.500 0.6414 0.02419 0.01602 -0.0486 0.4271 1.0000
3.750 0.6656 0.02451 0.01616 -0.0477 0.4231 1.0000
4.000 0.6867 0.02520 0.01677 -0.0467 0.4188 1.0000
4.250 0.7023 0.02616 0.01783 -0.0451 0.4132 1.0000
4.500 0.7231 0.02681 0.01845 -0.0440 0.4087 1.0000
4.750 0.7469 0.02726 0.01880 -0.0432 0.4052 1.0000
5.000 0.7731 0.02766 0.01904 -0.0426 0.4022 1.0000
5.250 0.7857 0.02903 0.02057 -0.0409 0.3976 1.0000
5.500 0.7995 0.03028 0.02192 -0.0394 0.3928 1.0000
5.750 0.8200 0.03104 0.02266 -0.0384 0.3892 1.0000
6.000 0.8427 0.03170 0.02327 -0.0376 0.3864 1.0000
6.250 0.8685 0.03225 0.02373 -0.0371 0.3841 1.0000
6.500 0.8846 0.03366 0.02518 -0.0359 0.3814 1.0000
6.750 0.8665 0.03759 0.02949 -0.0328 0.3770 1.0000
7.000 0.8287 0.04317 0.03538 -0.0293 0.3725 1.0000
7.250 0.5291 0.07865 0.07133 -0.0349 0.3804 1.0000
7.500 0.5468 0.08122 0.07388 -0.0349 0.3816 1.0000
7.750 0.5700 0.08346 0.07609 -0.0348 0.3824 1.0000
8.000 0.4585 0.09827 0.09111 -0.0424 0.4237 1.0000
8.250 0.4925 0.10109 0.09390 -0.0424 0.4219 1.0000
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Polar data table (+)
Polar graphs
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