EPPLER 540 AIRFOIL (e540-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 540 AIRFOIL (e540-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.47 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e540-il-1000000-n5.txt Download as CSV file: xf-e540-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6573 0.07349 0.07147 -0.0724 1.0000 0.0021
-14.250 -0.6840 0.06533 0.06316 -0.0765 1.0000 0.0021
-14.000 -0.7016 0.05802 0.05564 -0.0813 0.9991 0.0021
-13.750 -0.7342 0.04962 0.04690 -0.0847 0.9964 0.0021
-13.500 -0.7350 0.04706 0.04425 -0.0846 0.9889 0.0021
-13.250 -0.7563 0.04192 0.03882 -0.0843 0.9649 0.0021
-13.000 -0.7476 0.03737 0.03394 -0.0886 0.9531 0.0021
-12.750 -0.7227 0.03391 0.03019 -0.0943 0.9432 0.0021
-12.500 -0.6931 0.03022 0.02613 -0.1007 0.9328 0.0021
-12.250 -0.6596 0.02755 0.02312 -0.1062 0.9162 0.0021
-12.000 -0.6374 0.02586 0.02113 -0.1080 0.8900 0.0021
-11.750 -0.6248 0.02482 0.01987 -0.1070 0.8704 0.0021
-11.500 -0.6130 0.02389 0.01878 -0.1056 0.8558 0.0021
-11.000 -0.5896 0.02191 0.01647 -0.1024 0.8333 0.0021
-10.750 -0.5765 0.02104 0.01547 -0.1009 0.8242 0.0021
-10.250 -0.5473 0.01961 0.01382 -0.0982 0.8078 0.0021
-10.000 -0.5327 0.01893 0.01302 -0.0967 0.8003 0.0021
-9.750 -0.5174 0.01826 0.01226 -0.0953 0.7937 0.0022
-9.500 -0.5013 0.01771 0.01164 -0.0940 0.7874 0.0022
-9.250 -0.4853 0.01713 0.01098 -0.0927 0.7820 0.0022
-9.000 -0.4692 0.01658 0.01035 -0.0913 0.7764 0.0022
-8.750 -0.4521 0.01613 0.00984 -0.0901 0.7711 0.0022
-8.500 -0.4359 0.01560 0.00924 -0.0887 0.7660 0.0023
-8.250 -0.4195 0.01512 0.00870 -0.0873 0.7609 0.0023
-8.000 -0.4017 0.01474 0.00827 -0.0861 0.7565 0.0023
-7.750 -0.3840 0.01433 0.00782 -0.0849 0.7522 0.0024
-7.500 -0.3693 0.01380 0.00722 -0.0831 0.7479 0.0027
-7.000 -0.3342 0.01307 0.00642 -0.0804 0.7405 0.0032
-6.750 -0.3162 0.01274 0.00606 -0.0792 0.7366 0.0035
-6.500 -0.2985 0.01243 0.00571 -0.0778 0.7326 0.0037
-6.250 -0.2817 0.01211 0.00535 -0.0762 0.7291 0.0047
-6.000 -0.2648 0.01178 0.00501 -0.0747 0.7260 0.0058
-5.750 -0.2483 0.01148 0.00471 -0.0731 0.7227 0.0074
-5.500 -0.2345 0.01120 0.00441 -0.0709 0.7194 0.0104
-5.250 -0.2221 0.01098 0.00419 -0.0683 0.7163 0.0148
-5.000 -0.2042 0.01074 0.00397 -0.0668 0.7134 0.0210
-4.750 -0.1863 0.01046 0.00375 -0.0654 0.7104 0.0348
-4.500 -0.1674 0.01019 0.00354 -0.0641 0.7074 0.0516
-4.250 -0.1549 0.00964 0.00325 -0.0618 0.7046 0.1127
-4.000 -0.1412 0.00907 0.00294 -0.0597 0.7021 0.1857
-3.750 -0.1270 0.00841 0.00262 -0.0578 0.6996 0.2773
-3.500 -0.1155 0.00741 0.00216 -0.0557 0.6969 0.4193
-3.250 -0.1035 0.00616 0.00165 -0.0537 0.6941 0.6110
-3.000 -0.0766 0.00611 0.00170 -0.0537 0.6917 0.6619
-2.750 -0.0481 0.00616 0.00172 -0.0540 0.6895 0.6779
-2.500 -0.0195 0.00626 0.00178 -0.0543 0.6873 0.6899
-2.250 0.0094 0.00639 0.00192 -0.0547 0.6852 0.6994
-2.000 0.0383 0.00648 0.00198 -0.0550 0.6829 0.7062
-1.750 0.0673 0.00650 0.00198 -0.0555 0.6806 0.7078
-1.500 0.0961 0.00650 0.00195 -0.0559 0.6783 0.7085
-1.250 0.1248 0.00651 0.00192 -0.0564 0.6759 0.7092
-1.000 0.1535 0.00652 0.00189 -0.0568 0.6737 0.7098
-0.750 0.1823 0.00653 0.00188 -0.0572 0.6715 0.7106
-0.500 0.2113 0.00653 0.00187 -0.0577 0.6690 0.7114
-0.250 0.2400 0.00654 0.00185 -0.0582 0.6659 0.7122
0.000 0.2685 0.00655 0.00184 -0.0585 0.6625 0.7129
0.250 0.2966 0.00658 0.00183 -0.0589 0.6591 0.7136
0.500 0.3253 0.00658 0.00183 -0.0593 0.6558 0.7143
0.750 0.3538 0.00659 0.00183 -0.0597 0.6519 0.7150
1.000 0.3820 0.00661 0.00183 -0.0600 0.6478 0.7157
1.250 0.4099 0.00664 0.00184 -0.0603 0.6437 0.7163
1.500 0.4383 0.00665 0.00186 -0.0607 0.6390 0.7170
1.750 0.4662 0.00668 0.00187 -0.0610 0.6340 0.7177
2.000 0.4939 0.00672 0.00189 -0.0612 0.6292 0.7183
2.250 0.5219 0.00673 0.00192 -0.0615 0.6235 0.7190
2.500 0.5490 0.00676 0.00195 -0.0616 0.6173 0.7196
2.750 0.5765 0.00679 0.00199 -0.0618 0.6104 0.7203
3.000 0.6030 0.00684 0.00204 -0.0618 0.6023 0.7209
3.250 0.6299 0.00689 0.00209 -0.0619 0.5928 0.7215
3.500 0.6558 0.00696 0.00215 -0.0617 0.5813 0.7222
3.750 0.6806 0.00707 0.00223 -0.0614 0.5655 0.7228
4.000 0.7037 0.00722 0.00233 -0.0607 0.5453 0.7235
4.250 0.7250 0.00744 0.00246 -0.0596 0.5181 0.7242
4.500 0.7434 0.00777 0.00264 -0.0580 0.4823 0.7250
4.750 0.7592 0.00818 0.00288 -0.0560 0.4419 0.7258
5.000 0.7745 0.00861 0.00316 -0.0538 0.4035 0.7267
5.250 0.7906 0.00899 0.00341 -0.0519 0.3706 0.7277
5.500 0.8047 0.00935 0.00365 -0.0495 0.3399 0.7287
5.750 0.8173 0.00972 0.00390 -0.0468 0.3107 0.7295
6.000 0.8286 0.01015 0.00419 -0.0439 0.2799 0.7303
6.250 0.8415 0.01059 0.00452 -0.0414 0.2525 0.7311
6.500 0.8543 0.01104 0.00488 -0.0390 0.2276 0.7318
6.750 0.8633 0.01164 0.00531 -0.0359 0.1943 0.7325
7.000 0.8739 0.01217 0.00573 -0.0332 0.1677 0.7334
7.250 0.8866 0.01265 0.00614 -0.0310 0.1493 0.7343
7.500 0.8998 0.01314 0.00657 -0.0289 0.1318 0.7352
7.750 0.9115 0.01370 0.00707 -0.0266 0.1134 0.7360
8.000 0.9234 0.01428 0.00758 -0.0244 0.0976 0.7369
8.250 0.9365 0.01483 0.00811 -0.0226 0.0850 0.7378
8.500 0.9502 0.01539 0.00865 -0.0208 0.0742 0.7388
8.750 0.9640 0.01596 0.00920 -0.0191 0.0649 0.7398
9.000 0.9764 0.01662 0.00983 -0.0174 0.0546 0.7409
9.250 0.9878 0.01736 0.01052 -0.0155 0.0436 0.7419
9.500 0.9987 0.01815 0.01126 -0.0136 0.0333 0.7429
9.750 1.0116 0.01887 0.01196 -0.0121 0.0279 0.7438
10.000 1.0247 0.01959 0.01268 -0.0107 0.0228 0.7446
10.250 1.0376 0.02035 0.01344 -0.0093 0.0192 0.7455
10.500 1.0510 0.02110 0.01421 -0.0080 0.0163 0.7462
11.000 1.0775 0.02266 0.01581 -0.0056 0.0126 0.7480
11.250 1.0912 0.02343 0.01662 -0.0045 0.0113 0.7490
11.500 1.1041 0.02427 0.01750 -0.0034 0.0102 0.7500
11.750 1.1152 0.02524 0.01848 -0.0021 0.0082 0.7509
12.000 1.1280 0.02612 0.01941 -0.0011 0.0073 0.7519
12.250 1.1392 0.02713 0.02045 0.0000 0.0059 0.7530
12.500 1.1501 0.02818 0.02155 0.0011 0.0049 0.7540
12.750 1.1611 0.02925 0.02267 0.0021 0.0043 0.7550
13.000 1.1710 0.03043 0.02388 0.0032 0.0035 0.7562
13.250 1.1806 0.03166 0.02515 0.0042 0.0029 0.7574
13.500 1.1909 0.03286 0.02642 0.0051 0.0027 0.7586
13.750 1.2010 0.03412 0.02773 0.0059 0.0025 0.7596
14.000 1.2103 0.03547 0.02913 0.0067 0.0023 0.7606
14.500 1.2246 0.03859 0.03239 0.0084 0.0018 0.7626
14.750 1.2313 0.04026 0.03414 0.0091 0.0016 0.7637
15.000 1.2401 0.04178 0.03572 0.0096 0.0015 0.7649
15.250 1.2462 0.04358 0.03763 0.0102 0.0014 0.7660
15.500 1.2532 0.04533 0.03946 0.0106 0.0014 0.7673
15.750 1.2597 0.04718 0.04138 0.0110 0.0014 0.7685
16.000 1.2643 0.04927 0.04355 0.0113 0.0012 0.7697
16.250 1.2683 0.05149 0.04586 0.0115 0.0012 0.7709
16.500 1.2720 0.05380 0.04825 0.0116 0.0011 0.7721
16.750 1.2748 0.05625 0.05078 0.0116 0.0010 0.7733
17.000 1.2782 0.05873 0.05335 0.0115 0.0011 0.7744
17.250 1.2759 0.06195 0.05667 0.0113 0.0009 0.7753
17.500 1.2748 0.06512 0.05995 0.0108 0.0009 0.7766
17.750 1.2743 0.06830 0.06323 0.0102 0.0009 0.7778
18.000 1.2710 0.07196 0.06702 0.0094 0.0009 0.7791
18.250 1.2652 0.07610 0.07129 0.0083 0.0008 0.7804
18.500 1.2565 0.08083 0.07617 0.0068 0.0008 0.7817
18.750 1.2488 0.08556 0.08102 0.0051 0.0008 0.7830
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