EPPLER 858 AIRFOIL (e858-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 858 AIRFOIL (e858-il) Reynolds number: 100,000 Max Cl/Cd: 21.5 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e858-il-100000.txt Download as CSV file: xf-e858-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 858 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.5096 0.08728 0.08197 -0.0763 1.0000 0.0651
-13.250 -0.5461 0.08042 0.07502 -0.0788 1.0000 0.0644
-13.000 -0.5851 0.07427 0.06874 -0.0806 1.0000 0.0637
-12.750 -0.6239 0.06923 0.06357 -0.0813 1.0000 0.0632
-12.500 -0.6606 0.06534 0.05956 -0.0806 1.0000 0.0629
-12.250 -0.7681 0.05983 0.05350 -0.0779 1.0000 0.0596
-12.000 -0.7959 0.05876 0.05244 -0.0741 1.0000 0.0598
-11.750 -0.7620 0.05809 0.05201 -0.0751 0.9971 0.0621
-11.500 -0.7569 0.05460 0.04819 -0.0807 0.9846 0.0638
-11.250 -0.7529 0.05102 0.04409 -0.0844 0.9711 0.0652
-11.000 -0.7180 0.04878 0.04189 -0.0874 0.9613 0.0680
-10.750 -0.6946 0.04609 0.03894 -0.0900 0.9494 0.0710
-10.500 -0.6618 0.04384 0.03665 -0.0926 0.9390 0.0746
-10.250 -0.6268 0.04149 0.03415 -0.0960 0.9307 0.0805
-10.000 -0.6011 0.03959 0.03213 -0.0974 0.9177 0.0864
-9.750 -0.5706 0.03786 0.03049 -0.0988 0.9057 0.0933
-9.500 -0.5312 0.03562 0.02815 -0.1023 0.8994 0.1041
-9.250 -0.5073 0.03403 0.02661 -0.1027 0.8857 0.1142
-9.000 -0.4742 0.03225 0.02503 -0.1043 0.8763 0.1275
-8.750 -0.4403 0.03044 0.02332 -0.1064 0.8669 0.1440
-8.500 -0.4094 0.02873 0.02165 -0.1080 0.8563 0.1634
-8.250 -0.3703 0.02694 0.01999 -0.1110 0.8471 0.1893
-8.000 -0.3366 0.02552 0.01880 -0.1130 0.8351 0.2186
-7.750 -0.2896 0.02431 0.01780 -0.1172 0.8252 0.2596
-7.500 -0.2581 0.02411 0.01770 -0.1178 0.8100 0.2943
-7.250 -0.2126 0.02441 0.01793 -0.1205 0.7969 0.3292
-7.000 -0.1648 0.02546 0.01899 -0.1224 0.7825 0.3528
-6.750 -0.1343 0.02630 0.01976 -0.1218 0.7665 0.3708
-6.500 -0.0980 0.02708 0.02037 -0.1223 0.7527 0.3886
-6.250 -0.0532 0.02857 0.02185 -0.1229 0.7384 0.4005
-6.000 -0.0305 0.02915 0.02234 -0.1211 0.7243 0.4124
-5.750 0.0053 0.02970 0.02265 -0.1218 0.7127 0.4268
-5.500 0.0284 0.03048 0.02345 -0.1193 0.6988 0.4343
-5.250 0.0623 0.03130 0.02414 -0.1189 0.6877 0.4443
-5.000 0.0774 0.03110 0.02382 -0.1170 0.6762 0.4552
-4.750 0.1143 0.03209 0.02473 -0.1164 0.6661 0.4627
-4.500 0.1196 0.03119 0.02365 -0.1144 0.6557 0.4757
-4.250 0.1616 0.03212 0.02447 -0.1145 0.6467 0.4816
-4.000 0.1709 0.03205 0.02439 -0.1115 0.6363 0.4904
-3.750 0.1924 0.03148 0.02362 -0.1113 0.6281 0.5004
-3.500 0.2173 0.03198 0.02410 -0.1096 0.6197 0.5062
-3.250 0.2317 0.03161 0.02362 -0.1081 0.6114 0.5157
-3.000 0.2582 0.03118 0.02299 -0.1084 0.6046 0.5238
-2.750 0.2770 0.03146 0.02329 -0.1062 0.5968 0.5290
-2.500 0.2941 0.03123 0.02299 -0.1048 0.5891 0.5364
-2.250 0.3202 0.03052 0.02199 -0.1061 0.5830 0.5450
-2.000 0.3398 0.03066 0.02216 -0.1042 0.5763 0.5492
-1.750 0.3558 0.03070 0.02221 -0.1022 0.5694 0.5544
-1.500 0.3809 0.03040 0.02175 -0.1024 0.5637 0.5612
-1.250 0.4140 0.03005 0.02110 -0.1045 0.5590 0.5681
-1.000 0.4219 0.03022 0.02143 -0.1010 0.5526 0.5718
-0.750 0.4402 0.03027 0.02148 -0.0995 0.5466 0.5765
-0.500 0.4677 0.03012 0.02117 -0.0999 0.5416 0.5821
-0.250 0.5024 0.03002 0.02077 -0.1021 0.5371 0.5895
0.000 0.5078 0.03026 0.02120 -0.0984 0.5316 0.5932
0.250 0.5234 0.03050 0.02149 -0.0965 0.5265 0.5977
0.500 0.5474 0.03058 0.02150 -0.0961 0.5221 0.6029
0.750 0.5797 0.03058 0.02131 -0.0975 0.5184 0.6096
1.000 0.6001 0.03090 0.02159 -0.0967 0.5143 0.6150
1.250 0.6032 0.03144 0.02231 -0.0928 0.5092 0.6194
1.500 0.6190 0.03179 0.02268 -0.0911 0.5046 0.6249
1.750 0.6442 0.03197 0.02277 -0.0912 0.5008 0.6312
2.000 0.6756 0.03210 0.02278 -0.0922 0.4977 0.6375
2.250 0.7008 0.03259 0.02324 -0.0920 0.4947 0.6435
2.500 0.6857 0.03382 0.02472 -0.0857 0.4903 0.6485
2.750 0.6824 0.03489 0.02588 -0.0815 0.4859 0.6546
3.000 0.6976 0.03540 0.02640 -0.0800 0.4822 0.6606
3.250 0.7255 0.03557 0.02655 -0.0801 0.4791 0.6674
3.500 0.7640 0.03569 0.02654 -0.0821 0.4764 0.6766
3.750 0.7701 0.03684 0.02776 -0.0794 0.4735 0.6835
4.000 0.2423 0.07522 0.06728 -0.0425 0.4606 0.6524
4.250 0.2687 0.07600 0.06801 -0.0427 0.4581 0.6600
4.500 0.2791 0.07813 0.07018 -0.0425 0.4572 0.6661
4.750 0.2981 0.07984 0.07187 -0.0427 0.4561 0.6737
5.000 0.3225 0.08140 0.07340 -0.0431 0.4552 0.6819
5.250 0.3459 0.08314 0.07519 -0.0431 0.4545 0.6906
5.500 0.2433 0.09733 0.08962 -0.0449 0.4966 0.6853
5.750 0.2068 0.09893 0.09128 -0.0429 0.4894 0.6876
6.000 0.2179 0.10029 0.09264 -0.0427 0.4828 0.6964
6.250 0.2422 0.10193 0.09430 -0.0431 0.4792 0.7073
6.500 0.2760 0.10411 0.09648 -0.0441 0.4769 0.7208
6.750 0.3162 0.10704 0.09945 -0.0457 0.4755 0.7359
7.000 0.2679 0.10780 0.10028 -0.0437 0.4648 0.7382
7.250 0.2879 0.10953 0.10206 -0.0443 0.4606 0.7537
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