EPPLER 542 AIRFOIL (e542-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 542 AIRFOIL (e542-il) Reynolds number: 500,000 Max Cl/Cd: 78.54 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e542-il-500000-n5.txt Download as CSV file: xf-e542-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.6197 0.07926 0.07660 -0.0629 1.0000 0.0035
-14.000 -0.6521 0.06854 0.06570 -0.0697 1.0000 0.0034
-13.750 -0.6795 0.06125 0.05821 -0.0727 1.0000 0.0034
-13.500 -0.7014 0.05609 0.05290 -0.0735 1.0000 0.0034
-13.250 -0.7260 0.05106 0.04760 -0.0728 1.0000 0.0035
-13.000 -0.7451 0.04724 0.04358 -0.0712 1.0000 0.0034
-12.500 -0.7732 0.04108 0.03698 -0.0663 1.0000 0.0035
-12.250 -0.7850 0.03845 0.03413 -0.0632 1.0000 0.0035
-11.750 -0.7769 0.03330 0.02853 -0.0617 0.9882 0.0036
-11.500 -0.7637 0.03179 0.02692 -0.0615 0.9674 0.0038
-11.250 -0.7368 0.02987 0.02480 -0.0642 0.9523 0.0039
-10.750 -0.6603 0.02592 0.02035 -0.0732 0.9325 0.0041
-10.500 -0.6160 0.02427 0.01847 -0.0785 0.9192 0.0042
-10.250 -0.5755 0.02307 0.01705 -0.0826 0.9007 0.0045
-10.000 -0.5468 0.02197 0.01571 -0.0840 0.8790 0.0045
-9.750 -0.5256 0.02133 0.01490 -0.0837 0.8605 0.0046
-9.250 -0.4910 0.01988 0.01315 -0.0812 0.8313 0.0048
-9.000 -0.4705 0.01965 0.01280 -0.0804 0.8195 0.0053
-8.750 -0.4547 0.01893 0.01198 -0.0789 0.8085 0.0055
-8.500 -0.4390 0.01827 0.01122 -0.0773 0.7976 0.0056
-8.250 -0.4205 0.01787 0.01076 -0.0761 0.7880 0.0059
-8.000 -0.4033 0.01739 0.01018 -0.0747 0.7787 0.0062
-7.750 -0.3858 0.01690 0.00962 -0.0733 0.7704 0.0063
-7.500 -0.3683 0.01645 0.00909 -0.0719 0.7625 0.0065
-7.250 -0.3503 0.01601 0.00859 -0.0706 0.7552 0.0069
-7.000 -0.3321 0.01563 0.00813 -0.0692 0.7475 0.0070
-6.750 -0.3144 0.01522 0.00765 -0.0678 0.7406 0.0076
-6.500 -0.2962 0.01485 0.00723 -0.0664 0.7333 0.0084
-6.250 -0.2780 0.01451 0.00683 -0.0650 0.7270 0.0097
-6.000 -0.2597 0.01417 0.00646 -0.0636 0.7207 0.0116
-5.750 -0.2425 0.01381 0.00609 -0.0620 0.7147 0.0166
-5.500 -0.2246 0.01349 0.00577 -0.0606 0.7093 0.0229
-5.250 -0.2077 0.01315 0.00546 -0.0589 0.7033 0.0344
-5.000 -0.1938 0.01272 0.00513 -0.0568 0.6977 0.0595
-4.750 -0.1816 0.01226 0.00481 -0.0544 0.6923 0.0937
-4.500 -0.1729 0.01175 0.00448 -0.0513 0.6868 0.1390
-4.250 -0.1712 0.01127 0.00420 -0.0468 0.6819 0.1936
-4.000 -0.1689 0.01069 0.00390 -0.0424 0.6774 0.2680
-3.750 -0.1685 0.00991 0.00352 -0.0378 0.6726 0.3685
-3.500 -0.1738 0.00876 0.00296 -0.0322 0.6678 0.5144
-3.250 -0.1683 0.00816 0.00313 -0.0278 0.6635 0.6926
-3.000 -0.1412 0.00837 0.00331 -0.0276 0.6593 0.7223
-2.750 -0.1137 0.00861 0.00349 -0.0274 0.6551 0.7388
-2.500 -0.0858 0.00894 0.00377 -0.0273 0.6512 0.7499
-2.250 -0.0589 0.00926 0.00398 -0.0270 0.6476 0.7607
-2.000 -0.0286 0.00981 0.00456 -0.0269 0.6439 0.7662
-1.750 -0.0006 0.00993 0.00464 -0.0270 0.6398 0.7690
-1.500 0.0267 0.00989 0.00453 -0.0272 0.6360 0.7704
-1.250 0.0539 0.00985 0.00441 -0.0274 0.6326 0.7718
-1.000 0.0813 0.00980 0.00428 -0.0276 0.6294 0.7731
-0.750 0.1088 0.00973 0.00417 -0.0279 0.6257 0.7745
-0.500 0.1363 0.00967 0.00405 -0.0282 0.6219 0.7756
-0.250 0.1640 0.00963 0.00395 -0.0285 0.6186 0.7764
0.000 0.1916 0.00963 0.00389 -0.0287 0.6153 0.7770
0.250 0.2195 0.00962 0.00387 -0.0289 0.6120 0.7776
0.500 0.2474 0.00961 0.00386 -0.0292 0.6084 0.7783
0.750 0.2751 0.00961 0.00384 -0.0294 0.6048 0.7788
1.000 0.3027 0.00963 0.00382 -0.0296 0.6014 0.7794
1.250 0.3302 0.00965 0.00381 -0.0298 0.5981 0.7800
1.500 0.3580 0.00964 0.00382 -0.0301 0.5943 0.7806
1.750 0.3854 0.00965 0.00382 -0.0303 0.5900 0.7812
2.000 0.4126 0.00967 0.00382 -0.0304 0.5855 0.7818
2.250 0.4397 0.00970 0.00383 -0.0306 0.5810 0.7826
2.500 0.4670 0.00971 0.00386 -0.0307 0.5761 0.7834
2.750 0.4940 0.00973 0.00389 -0.0309 0.5713 0.7842
3.000 0.5208 0.00977 0.00390 -0.0310 0.5667 0.7849
3.250 0.5479 0.00978 0.00394 -0.0311 0.5614 0.7857
3.500 0.5746 0.00980 0.00398 -0.0312 0.5557 0.7864
3.750 0.6008 0.00986 0.00400 -0.0312 0.5503 0.7871
4.000 0.6276 0.00987 0.00406 -0.0313 0.5441 0.7879
4.250 0.6535 0.00992 0.00411 -0.0312 0.5372 0.7886
4.500 0.6796 0.00996 0.00417 -0.0312 0.5303 0.7894
4.750 0.7051 0.01001 0.00423 -0.0310 0.5220 0.7901
5.000 0.7305 0.01008 0.00431 -0.0309 0.5136 0.7908
5.250 0.7546 0.01017 0.00438 -0.0305 0.5034 0.7916
5.500 0.7792 0.01025 0.00448 -0.0302 0.4917 0.7923
5.750 0.8020 0.01036 0.00459 -0.0295 0.4780 0.7931
6.000 0.8233 0.01050 0.00472 -0.0285 0.4612 0.7938
6.250 0.8420 0.01072 0.00488 -0.0270 0.4399 0.7944
6.500 0.8583 0.01100 0.00510 -0.0252 0.4131 0.7951
6.750 0.8718 0.01135 0.00535 -0.0228 0.3851 0.7959
7.000 0.8817 0.01174 0.00564 -0.0197 0.3580 0.7968
7.250 0.8901 0.01219 0.00598 -0.0164 0.3308 0.7977
7.500 0.9002 0.01268 0.00639 -0.0136 0.3049 0.7987
7.750 0.9103 0.01321 0.00684 -0.0109 0.2819 0.7996
8.000 0.9205 0.01374 0.00731 -0.0082 0.2595 0.8006
8.250 0.9288 0.01437 0.00785 -0.0054 0.2367 0.8017
8.500 0.9381 0.01498 0.00840 -0.0029 0.2160 0.8027
8.750 0.9448 0.01573 0.00905 -0.0001 0.1941 0.8039
9.000 0.9515 0.01652 0.00976 0.0026 0.1726 0.8052
9.250 0.9583 0.01735 0.01052 0.0050 0.1532 0.8064
9.500 0.9651 0.01825 0.01134 0.0073 0.1359 0.8074
9.750 0.9747 0.01906 0.01213 0.0092 0.1237 0.8082
10.000 0.9824 0.01997 0.01302 0.0111 0.1102 0.8091
10.250 0.9910 0.02089 0.01392 0.0129 0.0993 0.8100
10.500 0.9983 0.02191 0.01493 0.0147 0.0875 0.8110
10.750 1.0066 0.02293 0.01596 0.0163 0.0786 0.8119
11.000 1.0142 0.02404 0.01706 0.0179 0.0698 0.8129
11.250 1.0218 0.02519 0.01821 0.0193 0.0617 0.8139
11.500 1.0302 0.02633 0.01936 0.0206 0.0547 0.8149
11.750 1.0361 0.02766 0.02067 0.0220 0.0464 0.8159
12.000 1.0438 0.02893 0.02196 0.0231 0.0408 0.8170
12.250 1.0500 0.03033 0.02336 0.0243 0.0347 0.8180
12.500 1.0562 0.03177 0.02481 0.0253 0.0294 0.8191
12.750 1.0634 0.03319 0.02625 0.0262 0.0262 0.8201
13.000 1.0701 0.03470 0.02778 0.0270 0.0224 0.8213
13.250 1.0757 0.03633 0.02943 0.0278 0.0186 0.8225
13.500 1.0828 0.03789 0.03103 0.0284 0.0164 0.8235
14.000 1.0954 0.04126 0.03450 0.0295 0.0126 0.8255
14.250 1.1016 0.04301 0.03630 0.0299 0.0110 0.8265
14.500 1.1076 0.04482 0.03818 0.0302 0.0099 0.8275
14.750 1.1137 0.04667 0.04011 0.0305 0.0091 0.8285
15.000 1.1194 0.04861 0.04213 0.0306 0.0080 0.8296
15.250 1.1244 0.05068 0.04427 0.0307 0.0075 0.8307
15.500 1.1287 0.05285 0.04652 0.0307 0.0060 0.8318
15.750 1.1329 0.05512 0.04886 0.0306 0.0056 0.8329
16.000 1.1364 0.05752 0.05135 0.0304 0.0049 0.8341
16.250 1.1400 0.05996 0.05387 0.0301 0.0045 0.8352
16.500 1.1415 0.06269 0.05668 0.0296 0.0040 0.8363
16.750 1.1435 0.06547 0.05955 0.0291 0.0035 0.8374
17.000 1.1435 0.06855 0.06273 0.0284 0.0031 0.8384
17.250 1.1435 0.07173 0.06600 0.0276 0.0029 0.8394
17.750 1.1401 0.07871 0.07320 0.0255 0.0022 0.8415
18.000 1.1393 0.08222 0.07683 0.0242 0.0022 0.8426
18.250 1.1376 0.08594 0.08067 0.0228 0.0022 0.8437
18.500 1.1337 0.09008 0.08494 0.0212 0.0021 0.8447
18.750 1.1262 0.09486 0.08983 0.0192 0.0018 0.8458
19.000 1.1193 0.09968 0.09478 0.0171 0.0017 0.8470
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Polar data table (+)
Polar graphs
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