EPPLER 540 AIRFOIL (e540-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 540 AIRFOIL (e540-il) Reynolds number: 100,000 Max Cl/Cd: 33.41 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e540-il-100000-n5.txt Download as CSV file: xf-e540-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 540 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4603 0.09250 0.08743 -0.0708 1.0000 0.0150
-12.250 -0.4745 0.08706 0.08200 -0.0730 1.0000 0.0147
-12.000 -0.4987 0.08092 0.07579 -0.0752 1.0000 0.0147
-11.750 -0.5148 0.07710 0.07197 -0.0755 1.0000 0.0144
-11.500 -0.5359 0.07344 0.06829 -0.0748 1.0000 0.0141
-11.250 -0.5641 0.07010 0.06489 -0.0726 1.0000 0.0142
-11.000 -0.5880 0.06741 0.06213 -0.0702 0.9986 0.0141
-10.750 -0.5971 0.06234 0.05678 -0.0726 0.9894 0.0141
-10.500 -0.6045 0.05806 0.05220 -0.0737 0.9791 0.0141
-10.250 -0.6092 0.05418 0.04796 -0.0741 0.9688 0.0142
-10.000 -0.6109 0.05071 0.04407 -0.0739 0.9588 0.0146
-9.750 -0.6098 0.04789 0.04080 -0.0728 0.9489 0.0149
-9.250 -0.5884 0.04202 0.03433 -0.0725 0.9350 0.0160
-9.000 -0.5670 0.03967 0.03167 -0.0734 0.9303 0.0169
-8.750 -0.5454 0.03741 0.02909 -0.0734 0.9241 0.0173
-8.500 -0.5149 0.03499 0.02634 -0.0745 0.9199 0.0180
-8.250 -0.4734 0.03260 0.02366 -0.0769 0.9181 0.0191
-8.000 -0.4314 0.03075 0.02158 -0.0792 0.9164 0.0203
-7.750 -0.3967 0.02934 0.02001 -0.0804 0.9131 0.0224
-7.500 -0.3738 0.02821 0.01885 -0.0803 0.9068 0.0255
-7.250 -0.3456 0.02710 0.01761 -0.0809 0.9024 0.0295
-7.000 -0.3264 0.02606 0.01650 -0.0801 0.8960 0.0330
-6.500 -0.2832 0.02420 0.01467 -0.0794 0.8855 0.0595
-6.250 -0.2706 0.02346 0.01418 -0.0772 0.8783 0.0969
-6.000 -0.2560 0.02239 0.01369 -0.0758 0.8734 0.1945
-5.750 -0.2109 0.02436 0.01785 -0.0730 0.8726 0.5730
-5.500 -0.2112 0.02451 0.01790 -0.0684 0.8640 0.6201
-5.250 -0.2060 0.02461 0.01783 -0.0648 0.8581 0.6531
-5.000 -0.2101 0.02503 0.01815 -0.0590 0.8500 0.6733
-4.750 -0.1936 0.02563 0.01856 -0.0566 0.8455 0.6926
-4.500 -0.1432 0.02721 0.01990 -0.0583 0.8440 0.7107
-4.250 -0.0986 0.02850 0.02097 -0.0594 0.8412 0.7278
-4.000 -0.0720 0.02888 0.02121 -0.0588 0.8365 0.7371
-3.750 -0.0701 0.02876 0.02097 -0.0547 0.8313 0.7473
-3.500 -0.0282 0.02864 0.02066 -0.0574 0.8294 0.7495
-3.250 -0.0061 0.02869 0.02060 -0.0566 0.8245 0.7534
-3.000 -0.0107 0.02854 0.02037 -0.0514 0.8185 0.7620
-2.750 0.0242 0.02837 0.02006 -0.0530 0.8161 0.7640
-2.500 0.0474 0.02832 0.01992 -0.0525 0.8124 0.7672
-2.250 0.0318 0.02822 0.01979 -0.0455 0.8054 0.7756
-2.000 0.0640 0.02805 0.01950 -0.0466 0.8028 0.7772
-1.750 0.0960 0.02785 0.01920 -0.0478 0.8007 0.7791
-1.500 0.0983 0.02802 0.01936 -0.0436 0.7944 0.7832
-1.250 0.0931 0.02773 0.01902 -0.0386 0.7893 0.7897
-1.000 0.1250 0.02756 0.01876 -0.0397 0.7872 0.7911
-0.750 0.1339 0.02772 0.01892 -0.0367 0.7816 0.7936
-0.500 0.1477 0.02768 0.01885 -0.0346 0.7771 0.7964
-0.250 0.1665 0.02746 0.01857 -0.0336 0.7741 0.7994
0.000 0.1572 0.02741 0.01851 -0.0278 0.7678 0.8042
0.250 0.1732 0.02743 0.01851 -0.0261 0.7631 0.8058
0.500 0.1990 0.02727 0.01832 -0.0262 0.7603 0.8072
0.750 0.2294 0.02706 0.01808 -0.0272 0.7583 0.8088
1.000 0.2158 0.02735 0.01841 -0.0205 0.7496 0.8124
1.250 0.2384 0.02713 0.01815 -0.0202 0.7463 0.8143
1.500 0.2664 0.02683 0.01782 -0.0209 0.7441 0.8165
2.000 0.2858 0.02698 0.01802 -0.0157 0.7321 0.8199
2.250 0.3202 0.02673 0.01778 -0.0173 0.7300 0.8208
2.500 0.3121 0.02715 0.01825 -0.0116 0.7206 0.8236
2.750 0.3435 0.02692 0.01804 -0.0127 0.7177 0.8249
3.250 0.3716 0.02699 0.01817 -0.0092 0.7054 0.8284
3.500 0.4087 0.02667 0.01790 -0.0112 0.7028 0.8293
4.000 0.4414 0.02667 0.01801 -0.0083 0.6898 0.8328
4.250 0.4841 0.02623 0.01765 -0.0110 0.6874 0.8334
4.500 0.4795 0.02660 0.01810 -0.0060 0.6766 0.8354
4.750 0.5218 0.02608 0.01766 -0.0085 0.6738 0.8360
5.250 0.5652 0.02580 0.01757 -0.0069 0.6597 0.8386
5.750 0.6144 0.02533 0.01729 -0.0062 0.6449 0.8416
6.000 0.6205 0.02563 0.01769 -0.0033 0.6332 0.8440
6.250 0.6352 0.02575 0.01794 -0.0018 0.6223 0.8458
6.500 0.6713 0.02505 0.01735 -0.0027 0.6152 0.8466
6.750 0.6858 0.02507 0.01749 -0.0008 0.6031 0.8480
7.000 0.6991 0.02517 0.01772 0.0012 0.5894 0.8496
7.250 0.7154 0.02519 0.01785 0.0027 0.5751 0.8512
7.500 0.7322 0.02523 0.01803 0.0041 0.5588 0.8529
7.750 0.7453 0.02550 0.01841 0.0058 0.5390 0.8550
8.000 0.7729 0.02507 0.01803 0.0060 0.5175 0.8568
8.250 0.7967 0.02491 0.01788 0.0066 0.4900 0.8587
8.500 0.8190 0.02484 0.01775 0.0075 0.4566 0.8603
8.750 0.8366 0.02504 0.01783 0.0089 0.4197 0.8618
9.000 0.8480 0.02564 0.01835 0.0108 0.3833 0.8636
9.250 0.8562 0.02650 0.01906 0.0128 0.3476 0.8655
9.500 0.8626 0.02753 0.01998 0.0148 0.3133 0.8676
9.750 0.8682 0.02871 0.02103 0.0166 0.2799 0.8698
10.000 0.8739 0.02999 0.02219 0.0182 0.2489 0.8721
10.250 0.8786 0.03135 0.02344 0.0198 0.2193 0.8744
10.500 0.8829 0.03271 0.02472 0.0216 0.1919 0.8767
10.750 0.8884 0.03411 0.02606 0.0230 0.1670 0.8793
11.000 0.8936 0.03563 0.02750 0.0242 0.1430 0.8820
11.250 0.8991 0.03723 0.02904 0.0253 0.1233 0.8846
11.500 0.9060 0.03884 0.03067 0.0261 0.1051 0.8871
11.750 0.9114 0.04047 0.03232 0.0271 0.0909 0.8894
12.000 0.9162 0.04222 0.03408 0.0281 0.0797 0.8920
12.250 0.9197 0.04414 0.03600 0.0290 0.0701 0.8949
12.500 0.9255 0.04600 0.03794 0.0296 0.0614 0.8979
12.750 0.9301 0.04804 0.04006 0.0302 0.0551 0.9010
13.000 0.9338 0.05006 0.04219 0.0309 0.0501 0.9043
13.250 0.9357 0.05230 0.04449 0.0316 0.0461 0.9082
13.500 0.9415 0.05434 0.04671 0.0320 0.0413 0.9126
13.750 0.9435 0.05674 0.04920 0.0323 0.0380 0.9173
14.000 0.9462 0.05916 0.05172 0.0327 0.0353 0.9225
14.250 0.9513 0.06149 0.05428 0.0327 0.0320 0.9289
14.500 0.9539 0.06416 0.05710 0.0323 0.0293 0.9368
14.750 0.9545 0.06722 0.06029 0.0317 0.0273 0.9467
15.000 0.9570 0.06988 0.06315 0.0314 0.0256 0.9696
15.250 0.9587 0.07296 0.06647 0.0306 0.0236 1.0000
15.500 0.9591 0.07652 0.07019 0.0293 0.0218 1.0000
15.750 0.9585 0.08025 0.07405 0.0278 0.0206 1.0000
16.000 0.9566 0.08423 0.07814 0.0263 0.0197 1.0000
16.500 0.9488 0.09322 0.08748 0.0230 0.0182 1.0000
16.750 0.9421 0.09843 0.09294 0.0207 0.0177 1.0000
17.000 0.9331 0.10419 0.09894 0.0178 0.0173 1.0000
17.250 0.9209 0.11075 0.10574 0.0142 0.0168 1.0000
17.500 0.9077 0.11773 0.11293 0.0101 0.0164 1.0000
17.750 0.8926 0.12542 0.12082 0.0056 0.0164 1.0000
18.000 0.8744 0.13421 0.12981 0.0002 0.0165 1.0000
18.250 0.8523 0.14455 0.14031 -0.0062 0.0168 1.0000
18.500 0.8295 0.15573 0.15161 -0.0129 0.0176 1.0000
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Polar data table (+)
Polar graphs
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