EPPLER 857 AIRFOIL (e857-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 857 AIRFOIL (e857-il) Reynolds number: 100,000 Max Cl/Cd: 41.23 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e857-il-100000-n5.txt Download as CSV file: xf-e857-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.4338 0.10409 0.09871 -0.0647 1.0000 0.0299
-13.750 -0.5044 0.08741 0.08169 -0.0737 1.0000 0.0291
-13.500 -0.5342 0.08007 0.07416 -0.0770 1.0000 0.0291
-13.250 -0.5557 0.07469 0.06864 -0.0788 1.0000 0.0290
-13.000 -0.5733 0.07032 0.06415 -0.0799 1.0000 0.0292
-12.750 -0.5902 0.06641 0.06013 -0.0804 1.0000 0.0296
-12.500 -0.6062 0.06294 0.05655 -0.0804 1.0000 0.0301
-12.250 -0.6202 0.06003 0.05354 -0.0798 1.0000 0.0304
-12.000 -0.6302 0.05720 0.05058 -0.0796 0.9992 0.0308
-11.750 -0.6127 0.05399 0.04723 -0.0841 0.9935 0.0317
-11.500 -0.5941 0.05127 0.04446 -0.0879 0.9866 0.0329
-11.250 -0.5760 0.04860 0.04165 -0.0913 0.9791 0.0342
-11.000 -0.5596 0.04601 0.03889 -0.0941 0.9696 0.0360
-10.750 -0.5460 0.04383 0.03670 -0.0961 0.9571 0.0374
-10.500 -0.5338 0.04166 0.03440 -0.0976 0.9432 0.0396
-10.250 -0.5206 0.03963 0.03233 -0.0989 0.9296 0.0416
-10.000 -0.5073 0.03768 0.03032 -0.1002 0.9163 0.0440
-9.750 -0.4931 0.03578 0.02831 -0.1013 0.9039 0.0469
-9.500 -0.4780 0.03403 0.02650 -0.1023 0.8907 0.0502
-9.250 -0.4604 0.03244 0.02484 -0.1029 0.8768 0.0540
-9.000 -0.4378 0.03092 0.02323 -0.1041 0.8643 0.0595
-8.750 -0.4074 0.02940 0.02161 -0.1065 0.8544 0.0664
-8.500 -0.3833 0.02813 0.02029 -0.1076 0.8404 0.0738
-8.250 -0.3544 0.02691 0.01899 -0.1094 0.8274 0.0829
-8.000 -0.3193 0.02570 0.01768 -0.1123 0.8159 0.0949
-7.750 -0.2919 0.02463 0.01655 -0.1136 0.8017 0.1071
-7.500 -0.2664 0.02363 0.01551 -0.1145 0.7874 0.1209
-7.250 -0.2395 0.02266 0.01451 -0.1156 0.7739 0.1380
-7.000 -0.2113 0.02176 0.01357 -0.1168 0.7610 0.1612
-6.750 -0.1904 0.02095 0.01281 -0.1166 0.7471 0.1879
-6.500 -0.1667 0.02019 0.01215 -0.1167 0.7345 0.2259
-6.250 -0.1394 0.01970 0.01178 -0.1173 0.7228 0.2738
-6.000 -0.1153 0.01955 0.01166 -0.1168 0.7103 0.3122
-5.750 -0.0868 0.01958 0.01158 -0.1169 0.6992 0.3419
-5.500 -0.0597 0.01963 0.01147 -0.1167 0.6878 0.3651
-5.250 -0.0331 0.01973 0.01142 -0.1164 0.6771 0.3830
-5.000 -0.0050 0.01987 0.01140 -0.1162 0.6672 0.3972
-4.750 0.0207 0.01995 0.01134 -0.1157 0.6573 0.4092
-4.500 0.0483 0.02001 0.01118 -0.1157 0.6482 0.4211
-4.250 0.0736 0.02014 0.01124 -0.1150 0.6387 0.4304
-4.000 0.1001 0.02023 0.01112 -0.1147 0.6300 0.4432
-3.750 0.1259 0.02045 0.01130 -0.1140 0.6215 0.4528
-3.500 0.1514 0.02048 0.01115 -0.1136 0.6133 0.4632
-3.250 0.1790 0.02059 0.01118 -0.1133 0.6064 0.4699
-3.000 0.2033 0.02060 0.01107 -0.1127 0.5984 0.4781
-2.750 0.2302 0.02059 0.01092 -0.1126 0.5915 0.4844
-2.500 0.2557 0.02062 0.01088 -0.1121 0.5845 0.4895
-2.250 0.2807 0.02062 0.01077 -0.1116 0.5772 0.4955
-2.000 0.3087 0.02058 0.01051 -0.1119 0.5714 0.5018
-1.750 0.3332 0.02061 0.01053 -0.1112 0.5650 0.5057
-1.500 0.3585 0.02065 0.01051 -0.1108 0.5588 0.5106
-1.250 0.3859 0.02068 0.01039 -0.1108 0.5536 0.5163
-1.000 0.4119 0.02071 0.01029 -0.1107 0.5481 0.5218
-0.750 0.4359 0.02076 0.01035 -0.1100 0.5420 0.5257
-0.500 0.4620 0.02082 0.01034 -0.1097 0.5368 0.5308
-0.250 0.4901 0.02090 0.01028 -0.1099 0.5324 0.5366
0.000 0.5135 0.02099 0.01034 -0.1093 0.5270 0.5420
0.250 0.5382 0.02109 0.01045 -0.1087 0.5222 0.5462
0.500 0.5646 0.02119 0.01049 -0.1086 0.5180 0.5517
0.750 0.5932 0.02131 0.01048 -0.1089 0.5142 0.5581
1.000 0.6150 0.02146 0.01067 -0.1079 0.5092 0.5633
1.250 0.6385 0.02159 0.01083 -0.1072 0.5045 0.5683
1.500 0.6643 0.02173 0.01092 -0.1070 0.5005 0.5745
1.750 0.6927 0.02189 0.01097 -0.1073 0.4972 0.5815
2.000 0.7162 0.02209 0.01123 -0.1066 0.4935 0.5871
2.250 0.7378 0.02231 0.01150 -0.1057 0.4894 0.5936
2.500 0.7618 0.02252 0.01169 -0.1052 0.4854 0.6008
2.750 0.7868 0.02268 0.01187 -0.1048 0.4819 0.6072
3.000 0.8145 0.02286 0.01199 -0.1049 0.4788 0.6156
3.250 0.8358 0.02313 0.01232 -0.1040 0.4753 0.6233
3.500 0.8552 0.02342 0.01272 -0.1026 0.4716 0.6313
3.750 0.8776 0.02372 0.01304 -0.1019 0.4683 0.6404
4.000 0.9014 0.02396 0.01332 -0.1014 0.4651 0.6495
4.250 0.9281 0.02418 0.01353 -0.1014 0.4623 0.6607
4.500 0.9563 0.02441 0.01375 -0.1016 0.4597 0.6724
4.750 0.9694 0.02482 0.01434 -0.0993 0.4559 0.6840
5.000 0.9865 0.02521 0.01483 -0.0977 0.4525 0.6979
5.250 1.0062 0.02554 0.01528 -0.0965 0.4495 0.7134
5.500 1.0282 0.02582 0.01564 -0.0957 0.4468 0.7324
5.750 1.0527 0.02604 0.01592 -0.0953 0.4443 0.7557
6.000 1.0801 0.02620 0.01614 -0.0952 0.4421 0.7858
6.500 1.0995 0.02702 0.01752 -0.0896 0.4351 1.0000
6.750 1.1151 0.02762 0.01814 -0.0881 0.4322 1.0000
7.000 1.1350 0.02814 0.01865 -0.0873 0.4296 1.0000
7.250 1.1600 0.02856 0.01902 -0.0873 0.4272 1.0000
7.500 1.1903 0.02891 0.01931 -0.0881 0.4250 1.0000
7.750 1.1968 0.02973 0.02021 -0.0852 0.4221 1.0000
8.000 1.1923 0.03084 0.02146 -0.0808 0.4185 1.0000
8.250 1.1971 0.03182 0.02252 -0.0780 0.4154 1.0000
8.500 1.2088 0.03264 0.02339 -0.0762 0.4127 1.0000
8.750 1.2287 0.03321 0.02397 -0.0755 0.4103 1.0000
9.000 1.2577 0.03350 0.02423 -0.0760 0.4082 1.0000
9.250 1.2767 0.03416 0.02491 -0.0753 0.4058 1.0000
9.500 1.2276 0.03731 0.02835 -0.0667 0.4008 1.0000
9.750 1.2069 0.03989 0.03107 -0.0624 0.3967 1.0000
10.000 1.2137 0.04122 0.03246 -0.0608 0.3938 1.0000
10.250 1.2386 0.04156 0.03280 -0.0608 0.3918 1.0000
10.500 1.2767 0.04122 0.03245 -0.0618 0.3901 1.0000
10.750 1.0506 0.06191 0.05358 -0.0511 0.3703 1.0000
11.000 1.0989 0.05942 0.05109 -0.0510 0.3711 1.0000
11.250 1.1513 0.05675 0.04841 -0.0513 0.3719 1.0000
13.250 0.9289 0.10932 0.10163 -0.0551 0.2975 1.0000
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