EPPLER E852 AIRFOIL (e852-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER E852 AIRFOIL (e852-il) Reynolds number: 100,000 Max Cl/Cd: 57.3 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e852-il-100000-n5.txt Download as CSV file: xf-e852-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E852 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4281 0.09239 0.08755 -0.0453 1.0000 0.0176
-9.000 -0.4329 0.08846 0.08370 -0.0462 1.0000 0.0174
-8.750 -0.4390 0.08460 0.07992 -0.0469 1.0000 0.0172
-8.500 -0.4478 0.08061 0.07602 -0.0476 1.0000 0.0170
-8.250 -0.4598 0.07660 0.07211 -0.0482 1.0000 0.0168
-8.000 -0.4763 0.07283 0.06845 -0.0484 1.0000 0.0166
-7.750 -0.4980 0.06959 0.06529 -0.0481 1.0000 0.0165
-7.500 -0.5161 0.06611 0.06183 -0.0485 1.0000 0.0164
-7.250 -0.5130 0.05989 0.05542 -0.0547 0.9947 0.0161
-7.000 -0.4991 0.05330 0.04849 -0.0614 0.9868 0.0158
-6.750 -0.4798 0.04728 0.04203 -0.0667 0.9806 0.0155
-6.500 -0.4605 0.04221 0.03646 -0.0697 0.9734 0.0154
-6.250 -0.4337 0.03743 0.03107 -0.0728 0.9690 0.0153
-6.000 -0.4109 0.03375 0.02672 -0.0738 0.9626 0.0153
-5.750 -0.3815 0.03038 0.02276 -0.0752 0.9586 0.0155
-5.500 -0.3505 0.02759 0.01947 -0.0764 0.9554 0.0160
-5.250 -0.3245 0.02548 0.01701 -0.0762 0.9500 0.0169
-5.000 -0.2939 0.02386 0.01510 -0.0770 0.9464 0.0200
-4.750 -0.2623 0.02228 0.01345 -0.0784 0.9437 0.0250
-4.500 -0.2369 0.02097 0.01193 -0.0780 0.9382 0.0301
-4.250 -0.2069 0.01977 0.01071 -0.0791 0.9342 0.0456
-4.000 -0.1736 0.01859 0.00956 -0.0807 0.9314 0.0803
-3.750 -0.1457 0.01731 0.00868 -0.0818 0.9269 0.1678
-3.500 -0.1195 0.01601 0.00839 -0.0827 0.9226 0.4182
-3.250 -0.0877 0.01592 0.00835 -0.0834 0.9192 0.5058
-3.000 -0.0557 0.01592 0.00825 -0.0842 0.9161 0.5501
-2.750 -0.0314 0.01598 0.00825 -0.0834 0.9103 0.5816
-2.500 -0.0010 0.01600 0.00823 -0.0837 0.9068 0.6147
-2.250 0.0324 0.01596 0.00810 -0.0846 0.9044 0.6373
-2.000 0.0568 0.01598 0.00798 -0.0841 0.8985 0.6505
-1.750 0.0877 0.01593 0.00783 -0.0848 0.8947 0.6625
-1.500 0.1216 0.01586 0.00767 -0.0861 0.8921 0.6743
-1.250 0.1496 0.01586 0.00760 -0.0863 0.8876 0.6860
-1.000 0.1767 0.01587 0.00758 -0.0863 0.8828 0.6971
-0.750 0.2086 0.01582 0.00747 -0.0872 0.8796 0.7089
-0.500 0.2425 0.01575 0.00738 -0.0884 0.8773 0.7215
-0.250 0.2634 0.01588 0.00752 -0.0873 0.8705 0.7342
0.000 0.2941 0.01586 0.00752 -0.0879 0.8670 0.7483
0.250 0.3271 0.01580 0.00750 -0.0890 0.8645 0.7634
0.500 0.3480 0.01594 0.00769 -0.0878 0.8579 0.7801
0.750 0.3767 0.01592 0.00774 -0.0879 0.8540 0.7979
1.000 0.4083 0.01584 0.00774 -0.0885 0.8512 0.8190
1.250 0.4268 0.01596 0.00798 -0.0868 0.8441 0.8446
1.500 0.4557 0.01588 0.00806 -0.0868 0.8401 0.8770
1.750 0.4937 0.01573 0.00803 -0.0886 0.8374 0.9231
2.000 0.5232 0.01589 0.00827 -0.0895 0.8298 1.0000
2.250 0.5582 0.01591 0.00833 -0.0911 0.8257 1.0000
2.500 0.5840 0.01612 0.00864 -0.0910 0.8185 1.0000
2.750 0.6176 0.01611 0.00872 -0.0921 0.8129 1.0000
3.000 0.6442 0.01624 0.00893 -0.0919 0.8044 1.0000
3.250 0.6816 0.01604 0.00885 -0.0934 0.7977 1.0000
3.500 0.7091 0.01599 0.00892 -0.0930 0.7857 1.0000
3.750 0.7408 0.01569 0.00873 -0.0929 0.7704 1.0000
4.000 0.7657 0.01545 0.00868 -0.0915 0.7482 1.0000
4.250 0.7913 0.01521 0.00855 -0.0902 0.7229 1.0000
4.500 0.8157 0.01508 0.00852 -0.0888 0.6939 1.0000
4.750 0.8371 0.01501 0.00854 -0.0869 0.6532 1.0000
5.000 0.8589 0.01499 0.00834 -0.0847 0.5655 1.0000
5.250 0.8683 0.01609 0.00842 -0.0806 0.3942 1.0000
5.500 0.8711 0.01783 0.00931 -0.0766 0.2510 1.0000
5.750 0.8793 0.01948 0.01030 -0.0738 0.1459 1.0000
6.000 0.8929 0.02081 0.01134 -0.0717 0.0954 1.0000
6.250 0.9068 0.02216 0.01261 -0.0696 0.0622 1.0000
6.500 0.9200 0.02363 0.01399 -0.0673 0.0417 1.0000
6.750 0.9327 0.02524 0.01561 -0.0649 0.0282 1.0000
7.000 0.9479 0.02661 0.01704 -0.0631 0.0192 1.0000
7.250 0.9622 0.02855 0.01916 -0.0608 0.0164 1.0000
7.500 0.9824 0.03064 0.02144 -0.0595 0.0145 1.0000
7.750 1.0032 0.03243 0.02341 -0.0585 0.0122 1.0000
8.000 1.0200 0.03475 0.02587 -0.0575 0.0099 1.0000
8.250 1.0411 0.03733 0.02878 -0.0565 0.0089 1.0000
8.500 1.0597 0.04008 0.03194 -0.0552 0.0083 1.0000
8.750 1.0733 0.04335 0.03564 -0.0533 0.0081 1.0000
9.000 1.0808 0.04679 0.03953 -0.0508 0.0079 1.0000
9.250 1.0820 0.05026 0.04342 -0.0477 0.0079 1.0000
9.500 1.0775 0.05358 0.04711 -0.0442 0.0078 1.0000
9.750 1.0687 0.05701 0.05088 -0.0407 0.0078 1.0000
10.000 1.0570 0.06053 0.05469 -0.0376 0.0079 1.0000
10.250 1.0427 0.06428 0.05872 -0.0351 0.0079 1.0000
10.500 1.0267 0.06831 0.06300 -0.0334 0.0079 1.0000
10.750 1.0096 0.07271 0.06763 -0.0327 0.0080 1.0000
11.000 0.9905 0.07777 0.07289 -0.0330 0.0080 1.0000
11.250 0.9713 0.08336 0.07867 -0.0346 0.0081 1.0000
11.500 0.9518 0.08977 0.08523 -0.0375 0.0081 1.0000
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Polar data table (+)
Polar graphs
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