EPPLER 542 AIRFOIL (e542-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 542 AIRFOIL (e542-il) Reynolds number: 100,000 Max Cl/Cd: 47.38 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e542-il-100000.txt Download as CSV file: xf-e542-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 542 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3121 0.10333 0.09916 -0.0507 1.0000 0.1329
-10.750 -0.3658 0.09850 0.09449 -0.0543 1.0000 0.1387
-10.500 -0.4167 0.09505 0.09118 -0.0544 1.0000 0.1391
-10.250 -0.3895 0.09527 0.09150 -0.0465 1.0000 0.1420
-10.000 -0.4010 0.09512 0.09145 -0.0420 1.0000 0.1436
-9.750 -0.4176 0.09390 0.09030 -0.0390 1.0000 0.1455
-9.000 -0.6593 0.08395 0.07996 -0.0366 0.9974 0.1378
-8.750 -0.6440 0.07839 0.07441 -0.0391 0.9918 0.1442
-8.500 -0.6507 0.07496 0.07077 -0.0408 0.9808 0.1523
-7.750 -0.6680 0.05484 0.04831 -0.0356 0.9486 0.0699
-7.500 -0.6494 0.04732 0.03978 -0.0336 0.9436 0.0505
-7.250 -0.6287 0.04389 0.03620 -0.0332 0.9364 0.0486
-7.000 -0.6004 0.04029 0.03208 -0.0333 0.9308 0.0459
-6.750 -0.5588 0.03695 0.02810 -0.0351 0.9277 0.0448
-6.500 -0.5335 0.03543 0.02645 -0.0349 0.9202 0.0468
-6.250 -0.4937 0.03371 0.02437 -0.0367 0.9157 0.0504
-6.000 -0.4303 0.03103 0.02174 -0.0424 0.9151 0.0552
-5.750 -0.3721 0.02906 0.01985 -0.0473 0.9138 0.0693
-5.500 -0.3264 0.02693 0.01805 -0.0506 0.9117 0.0998
-5.250 -0.2877 0.02802 0.02269 -0.0444 0.9110 0.6966
-5.000 -0.1736 0.03424 0.02831 -0.0499 0.9129 0.7700
-4.750 -0.0747 0.03587 0.02951 -0.0586 0.9140 0.8034
-4.500 0.0028 0.03639 0.02971 -0.0655 0.9134 0.8393
-4.250 0.1893 0.03382 0.02672 -0.0898 0.9246 0.9525
-4.000 0.2532 0.03182 0.02452 -0.0986 0.9199 0.9799
-3.500 0.3669 0.02806 0.02042 -0.1142 0.9107 1.0000
-3.250 0.3893 0.02769 0.01995 -0.1149 0.9006 1.0000
-3.000 0.4232 0.02701 0.01915 -0.1178 0.8944 1.0000
-2.750 0.4407 0.02687 0.01896 -0.1172 0.8841 1.0000
-2.500 0.4695 0.02643 0.01841 -0.1188 0.8778 1.0000
-2.250 0.4835 0.02651 0.01846 -0.1175 0.8682 1.0000
-2.000 0.5082 0.02625 0.01813 -0.1181 0.8620 1.0000
-1.750 0.5220 0.02641 0.01827 -0.1167 0.8533 1.0000
-1.500 0.5435 0.02630 0.01812 -0.1165 0.8470 1.0000
-1.250 0.5601 0.02645 0.01824 -0.1156 0.8401 1.0000
-1.000 0.5766 0.02658 0.01836 -0.1145 0.8329 1.0000
-0.750 0.5998 0.02647 0.01821 -0.1145 0.8280 1.0000
-0.500 0.6098 0.02696 0.01875 -0.1125 0.8200 1.0000
-0.250 0.6294 0.02703 0.01879 -0.1118 0.8142 1.0000
0.000 0.6467 0.02725 0.01902 -0.1108 0.8085 1.0000
0.250 0.6588 0.02771 0.01952 -0.1090 0.8012 1.0000
0.500 0.6805 0.02772 0.01952 -0.1085 0.7963 1.0000
0.750 0.6908 0.02834 0.02021 -0.1065 0.7893 1.0000
1.000 0.7064 0.02866 0.02056 -0.1051 0.7829 1.0000
1.250 0.7308 0.02855 0.02044 -0.1049 0.7786 1.0000
1.500 0.7333 0.02959 0.02157 -0.1016 0.7698 1.0000
1.750 0.7543 0.02964 0.02166 -0.1009 0.7644 1.0000
2.000 0.7679 0.03011 0.02218 -0.0991 0.7579 1.0000
2.250 0.7781 0.03069 0.02282 -0.0967 0.7501 1.0000
2.500 0.8067 0.03032 0.02247 -0.0969 0.7458 1.0000
2.750 0.8035 0.03163 0.02388 -0.0927 0.7356 1.0000
3.000 0.8313 0.03123 0.02354 -0.0926 0.7305 1.0000
3.250 0.8319 0.03233 0.02473 -0.0889 0.7211 1.0000
3.500 0.8574 0.03201 0.02446 -0.0884 0.7150 1.0000
3.750 0.8642 0.03272 0.02528 -0.0854 0.7063 1.0000
4.000 0.8869 0.03249 0.02511 -0.0844 0.6992 1.0000
4.250 0.8993 0.03284 0.02555 -0.0821 0.6909 1.0000
4.500 0.9212 0.03256 0.02537 -0.0809 0.6830 1.0000
4.750 0.9342 0.03280 0.02570 -0.0785 0.6742 1.0000
5.000 0.9611 0.03217 0.02516 -0.0779 0.6664 1.0000
5.250 0.9708 0.03248 0.02558 -0.0749 0.6564 1.0000
5.500 1.0066 0.03131 0.02450 -0.0754 0.6492 1.0000
5.750 1.0142 0.03162 0.02493 -0.0721 0.6380 1.0000
6.000 1.0611 0.02978 0.02315 -0.0740 0.6311 1.0000
6.250 1.0663 0.03010 0.02361 -0.0702 0.6186 1.0000
6.500 1.0845 0.02967 0.02331 -0.0681 0.6071 1.0000
6.750 1.1202 0.02831 0.02202 -0.0684 0.5966 1.0000
7.000 1.1434 0.02750 0.02130 -0.0669 0.5833 1.0000
7.250 1.1574 0.02710 0.02103 -0.0641 0.5686 1.0000
7.500 1.1736 0.02653 0.02055 -0.0615 0.5528 1.0000
7.750 1.1895 0.02594 0.02006 -0.0588 0.5357 1.0000
8.000 1.1975 0.02565 0.01987 -0.0549 0.5168 1.0000
8.250 1.1979 0.02564 0.01997 -0.0499 0.4958 1.0000
8.500 1.2031 0.02539 0.01972 -0.0454 0.4724 1.0000
8.750 1.1963 0.02562 0.01999 -0.0393 0.4475 1.0000
9.000 1.1896 0.02582 0.02013 -0.0332 0.4217 1.0000
9.250 1.1743 0.02621 0.02044 -0.0257 0.3983 1.0000
9.500 1.1564 0.02670 0.02079 -0.0180 0.3768 1.0000
9.750 1.1372 0.02739 0.02140 -0.0106 0.3558 1.0000
10.000 1.1194 0.02820 0.02208 -0.0037 0.3347 1.0000
10.250 1.1023 0.02912 0.02286 0.0026 0.3145 1.0000
10.500 1.0848 0.03014 0.02381 0.0087 0.2953 1.0000
10.750 1.0678 0.03122 0.02480 0.0144 0.2769 1.0000
11.000 1.0512 0.03232 0.02581 0.0199 0.2594 1.0000
11.250 1.0352 0.03342 0.02683 0.0251 0.2430 1.0000
11.500 1.0197 0.03450 0.02783 0.0301 0.2278 1.0000
11.750 1.0040 0.03557 0.02882 0.0350 0.2132 1.0000
12.000 0.9889 0.03660 0.02978 0.0398 0.1995 1.0000
12.250 0.9760 0.03768 0.03078 0.0440 0.1859 1.0000
12.500 0.9677 0.03909 0.03211 0.0469 0.1708 1.0000
12.750 0.9649 0.04079 0.03374 0.0487 0.1550 1.0000
13.000 0.9645 0.04268 0.03558 0.0499 0.1396 1.0000
13.250 0.9668 0.04466 0.03749 0.0507 0.1251 1.0000
13.500 0.9715 0.04667 0.03947 0.0513 0.1121 1.0000
13.750 0.9788 0.04868 0.04146 0.0517 0.1007 1.0000
14.000 0.9887 0.05067 0.04342 0.0520 0.0906 1.0000
14.250 1.0040 0.05249 0.04513 0.0522 0.0812 1.0000
14.500 1.0071 0.05496 0.04783 0.0523 0.0749 1.0000
14.750 1.0210 0.05715 0.05004 0.0523 0.0684 1.0000
15.000 1.0248 0.05964 0.05264 0.0522 0.0633 1.0000
15.250 1.0343 0.06242 0.05554 0.0521 0.0586 1.0000
15.500 1.0319 0.06548 0.05881 0.0518 0.0549 1.0000
15.750 1.0421 0.06829 0.06162 0.0515 0.0509 1.0000
16.000 1.0290 0.07248 0.06616 0.0509 0.0490 1.0000
16.250 1.0253 0.07609 0.06996 0.0501 0.0467 1.0000
16.500 1.0366 0.07919 0.07301 0.0496 0.0437 1.0000
16.750 1.0181 0.08432 0.07847 0.0482 0.0433 1.0000
17.000 0.9959 0.09022 0.08469 0.0462 0.0429 1.0000
17.250 0.9755 0.09636 0.09111 0.0436 0.0427 1.0000
17.500 0.9540 0.10303 0.09802 0.0405 0.0427 1.0000
17.750 0.9305 0.11045 0.10567 0.0366 0.0429 1.0000
18.000 0.9089 0.11812 0.11351 0.0323 0.0432 1.0000
18.250 0.8884 0.12606 0.12160 0.0277 0.0436 1.0000
18.500 0.7210 0.17959 0.17518 -0.0005 0.0719 1.0000
18.750 0.7266 0.18456 0.18013 -0.0025 0.0708 1.0000
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