EPPLER 857 AIRFOIL (e857-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 857 AIRFOIL (e857-il) Reynolds number: 100,000 Max Cl/Cd: 25.86 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e857-il-100000.txt Download as CSV file: xf-e857-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 857 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2823 0.13961 0.13503 -0.0462 1.0000 0.1325
-12.000 -0.5155 0.08088 0.07600 -0.0760 1.0000 0.0586
-11.750 -0.5463 0.07647 0.07157 -0.0763 1.0000 0.0583
-11.500 -0.5714 0.07324 0.06837 -0.0752 1.0000 0.0579
-11.250 -0.6037 0.07062 0.06576 -0.0734 1.0000 0.0575
-11.000 -0.6372 0.06865 0.06381 -0.0709 1.0000 0.0571
-10.750 -0.6591 0.06421 0.05918 -0.0752 0.9936 0.0566
-10.500 -0.6747 0.05903 0.05356 -0.0814 0.9789 0.0570
-10.250 -0.6738 0.05413 0.04813 -0.0856 0.9651 0.0576
-10.000 -0.6670 0.04958 0.04289 -0.0886 0.9519 0.0586
-9.750 -0.6364 0.04686 0.04022 -0.0910 0.9426 0.0607
-9.500 -0.6038 0.04385 0.03693 -0.0943 0.9349 0.0632
-9.250 -0.5815 0.04091 0.03350 -0.0958 0.9233 0.0667
-9.000 -0.5512 0.03922 0.03188 -0.0972 0.9124 0.0710
-8.750 -0.5115 0.03675 0.02924 -0.1004 0.9066 0.0773
-8.500 -0.4864 0.03509 0.02732 -0.1008 0.8942 0.0843
-8.250 -0.4420 0.03295 0.02517 -0.1043 0.8897 0.0953
-8.000 -0.4173 0.03156 0.02381 -0.1043 0.8773 0.1054
-7.750 -0.3730 0.02938 0.02177 -0.1077 0.8732 0.1217
-7.500 -0.3477 0.02805 0.02054 -0.1077 0.8610 0.1370
-7.250 -0.3017 0.02616 0.01871 -0.1115 0.8561 0.1637
-7.000 -0.2751 0.02482 0.01760 -0.1120 0.8443 0.1899
-6.750 -0.2293 0.02298 0.01611 -0.1161 0.8381 0.2395
-6.500 -0.2017 0.02225 0.01571 -0.1165 0.8255 0.2993
-6.250 -0.1477 0.02253 0.01604 -0.1204 0.8182 0.3645
-6.000 -0.1174 0.02333 0.01681 -0.1197 0.8043 0.3922
-5.750 -0.0761 0.02415 0.01753 -0.1209 0.7930 0.4167
-5.500 -0.0349 0.02487 0.01813 -0.1220 0.7819 0.4368
-5.250 -0.0078 0.02554 0.01875 -0.1208 0.7688 0.4506
-5.000 0.0315 0.02590 0.01891 -0.1220 0.7588 0.4665
-4.750 0.0541 0.02612 0.01899 -0.1207 0.7461 0.4799
-4.500 0.0829 0.02660 0.01944 -0.1197 0.7350 0.4889
-4.250 0.1117 0.02651 0.01910 -0.1200 0.7248 0.5030
-4.000 0.1349 0.02721 0.01985 -0.1176 0.7140 0.5117
-3.750 0.1645 0.02726 0.01971 -0.1177 0.7053 0.5253
-3.500 0.1841 0.02760 0.02004 -0.1155 0.6952 0.5343
-3.250 0.2117 0.02727 0.01949 -0.1159 0.6867 0.5445
-3.000 0.2324 0.02746 0.01965 -0.1141 0.6777 0.5515
-2.750 0.2566 0.02705 0.01902 -0.1145 0.6693 0.5622
-2.500 0.2835 0.02719 0.01911 -0.1137 0.6623 0.5681
-2.250 0.3013 0.02713 0.01899 -0.1123 0.6539 0.5757
-2.000 0.3321 0.02682 0.01847 -0.1134 0.6477 0.5836
-1.750 0.3497 0.02694 0.01860 -0.1115 0.6401 0.5888
-1.500 0.3732 0.02682 0.01837 -0.1112 0.6329 0.5960
-1.250 0.4070 0.02658 0.01790 -0.1128 0.6276 0.6031
-1.000 0.4197 0.02678 0.01818 -0.1102 0.6203 0.6078
-0.750 0.4434 0.02678 0.01811 -0.1099 0.6143 0.6141
-0.500 0.4760 0.02665 0.01777 -0.1113 0.6095 0.6216
-0.250 0.4923 0.02689 0.01807 -0.1094 0.6036 0.6265
0.000 0.5113 0.02704 0.01822 -0.1082 0.5973 0.6322
0.250 0.5421 0.02700 0.01800 -0.1094 0.5924 0.6400
0.500 0.5707 0.02711 0.01806 -0.1095 0.5883 0.6457
0.750 0.5789 0.02760 0.01867 -0.1066 0.5824 0.6515
1.000 0.6018 0.02784 0.01883 -0.1064 0.5774 0.6588
1.250 0.6302 0.02790 0.01887 -0.1065 0.5734 0.6648
1.500 0.6603 0.02811 0.01898 -0.1072 0.5696 0.6727
1.750 0.6628 0.02885 0.01985 -0.1036 0.5636 0.6794
2.000 0.6808 0.02922 0.02027 -0.1021 0.5590 0.6857
2.250 0.7090 0.02943 0.02043 -0.1025 0.5554 0.6943
2.500 0.7426 0.02957 0.02050 -0.1037 0.5524 0.7028
2.750 0.7382 0.03074 0.02185 -0.0990 0.5475 0.7103
3.000 0.7413 0.03171 0.02293 -0.0957 0.5423 0.7187
3.250 0.7645 0.03201 0.02325 -0.0952 0.5385 0.7279
3.500 0.7977 0.03209 0.02328 -0.0962 0.5355 0.7392
3.750 0.8346 0.03228 0.02340 -0.0978 0.5330 0.7523
4.000 0.7351 0.03683 0.02843 -0.0805 0.5249 0.7566
4.250 0.7254 0.03854 0.03024 -0.0759 0.5202 0.7680
4.500 0.7759 0.03781 0.02950 -0.0788 0.5181 0.7855
4.750 0.8346 0.03702 0.02867 -0.0830 0.5162 0.8069
6.750 0.3912 0.09614 0.08913 -0.0617 0.5228 1.0000
7.000 0.4204 0.09808 0.09096 -0.0632 0.5184 1.0000
7.250 0.4596 0.10060 0.09337 -0.0651 0.5159 1.0000
7.500 0.5044 0.10387 0.09654 -0.0672 0.5146 1.0000
7.750 0.4522 0.10444 0.09716 -0.0642 0.5018 1.0000
8.000 0.4826 0.10662 0.09926 -0.0652 0.4986 1.0000
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Polar data table (+)
Polar graphs
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