EPPLER E850 AIRFOIL (e850-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E850 AIRFOIL (e850-il) Reynolds number: 500,000 Max Cl/Cd: 77.62 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e850-il-500000-n5.txt Download as CSV file: xf-e850-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E850 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5157 0.08839 0.08618 -0.0290 1.0000 0.0087
-8.500 -0.5204 0.08486 0.08268 -0.0296 1.0000 0.0090
-8.250 -0.5250 0.08067 0.07852 -0.0313 0.9996 0.0090
-8.000 -0.5192 0.07431 0.07218 -0.0384 0.9971 0.0090
-7.750 -0.5141 0.06541 0.06323 -0.0524 0.9926 0.0089
-7.500 -0.5056 0.05864 0.05631 -0.0603 0.9875 0.0091
-7.250 -0.4919 0.05275 0.05023 -0.0660 0.9839 0.0093
-5.500 -0.3571 0.02116 0.01624 -0.0747 0.9627 0.0057
-5.250 -0.3275 0.01968 0.01443 -0.0743 0.9610 0.0042
-5.000 -0.3003 0.01729 0.01177 -0.0744 0.9596 0.0036
-4.750 -0.2720 0.01511 0.00931 -0.0745 0.9584 0.0033
-4.500 -0.2430 0.01346 0.00746 -0.0748 0.9574 0.0031
-4.250 -0.2133 0.01222 0.00606 -0.0753 0.9565 0.0030
-4.000 -0.1827 0.01121 0.00490 -0.0761 0.9558 0.0029
-3.750 -0.1613 0.01060 0.00415 -0.0747 0.9516 0.0028
-3.500 -0.1329 0.01013 0.00352 -0.0749 0.9496 0.0028
-3.250 -0.1030 0.00981 0.00307 -0.0754 0.9481 0.0029
-3.000 -0.0722 0.00959 0.00271 -0.0761 0.9469 0.0029
-2.750 -0.0408 0.00942 0.00248 -0.0770 0.9459 0.0034
-2.500 -0.0091 0.00919 0.00228 -0.0780 0.9450 0.0213
-2.250 0.0206 0.00801 0.00196 -0.0795 0.9441 0.2569
-2.000 0.0492 0.00701 0.00201 -0.0806 0.9432 0.5418
-1.750 0.0742 0.00698 0.00201 -0.0800 0.9398 0.5595
-1.500 0.1023 0.00693 0.00196 -0.0802 0.9371 0.5710
-1.250 0.1324 0.00687 0.00191 -0.0807 0.9351 0.5793
-1.000 0.1639 0.00681 0.00185 -0.0816 0.9333 0.5874
-0.750 0.1962 0.00673 0.00180 -0.0827 0.9317 0.5957
-0.500 0.2298 0.00664 0.00174 -0.0840 0.9300 0.6038
0.000 0.2866 0.00650 0.00167 -0.0843 0.9198 0.6209
0.250 0.3181 0.00641 0.00163 -0.0850 0.9149 0.6298
0.500 0.3470 0.00633 0.00159 -0.0852 0.9070 0.6393
0.750 0.3762 0.00624 0.00157 -0.0854 0.8974 0.6492
1.000 0.4055 0.00616 0.00153 -0.0856 0.8841 0.6593
1.250 0.4343 0.00608 0.00148 -0.0856 0.8612 0.6701
1.500 0.4619 0.00606 0.00152 -0.0852 0.8223 0.6816
1.750 0.4859 0.00626 0.00150 -0.0841 0.7442 0.6938
2.000 0.4967 0.00711 0.00169 -0.0803 0.5879 0.7064
2.250 0.5073 0.00821 0.00206 -0.0771 0.4023 0.7200
2.500 0.5238 0.00916 0.00243 -0.0752 0.2436 0.7351
2.750 0.5447 0.00977 0.00275 -0.0741 0.1510 0.7523
3.000 0.5663 0.01033 0.00309 -0.0731 0.0778 0.7711
3.250 0.5889 0.01077 0.00344 -0.0721 0.0367 0.7923
3.500 0.6113 0.01118 0.00389 -0.0711 0.0122 0.8169
3.750 0.6313 0.01195 0.00492 -0.0690 0.0055 0.8466
4.000 0.6501 0.01254 0.00575 -0.0668 0.0052 0.8884
4.250 0.6773 0.01284 0.00621 -0.0667 0.0040 0.9913
4.500 0.7032 0.01299 0.00632 -0.0667 0.0026 1.0000
4.750 0.7248 0.01402 0.00746 -0.0654 0.0021 1.0000
5.000 0.7466 0.01525 0.00883 -0.0642 0.0018 1.0000
5.250 0.7704 0.01621 0.00992 -0.0634 0.0016 1.0000
5.500 0.7940 0.01776 0.01168 -0.0623 0.0014 1.0000
5.750 0.8175 0.02010 0.01436 -0.0610 0.0012 1.0000
6.000 0.8391 0.02325 0.01795 -0.0592 0.0012 1.0000
6.250 0.8566 0.02723 0.02244 -0.0565 0.0012 1.0000
6.500 0.8690 0.03229 0.02802 -0.0529 0.0012 1.0000
6.750 0.8784 0.03743 0.03359 -0.0493 0.0012 1.0000
7.000 0.8853 0.04246 0.03898 -0.0459 0.0013 1.0000
7.250 0.8898 0.04744 0.04426 -0.0427 0.0013 1.0000
7.500 0.8913 0.05242 0.04951 -0.0397 0.0014 1.0000
7.750 0.8902 0.05729 0.05461 -0.0370 0.0014 1.0000
8.000 0.8855 0.06213 0.05964 -0.0346 0.0015 1.0000
8.250 0.8786 0.06663 0.06429 -0.0326 0.0015 1.0000
8.500 0.8659 0.07081 0.06859 -0.0303 0.0015 1.0000
8.750 0.8491 0.07472 0.07259 -0.0283 0.0015 1.0000
9.000 0.8326 0.07916 0.07710 -0.0282 0.0015 1.0000
9.250 0.8168 0.08458 0.08257 -0.0306 0.0015 1.0000
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Polar data table (+)
Polar graphs
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