EPPLER 855 AIRFOIL (e855-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 855 AIRFOIL (e855-il) Reynolds number: 200,000 Max Cl/Cd: 76.37 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e855-il-200000.txt Download as CSV file: xf-e855-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 855 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4196 0.08563 0.08230 -0.0605 1.0000 0.0306
-10.500 -0.4306 0.08118 0.07791 -0.0611 1.0000 0.0297
-10.250 -0.4586 0.07411 0.07085 -0.0641 1.0000 0.0289
-10.000 -0.4882 0.06860 0.06533 -0.0659 1.0000 0.0283
-9.750 -0.5227 0.06443 0.06116 -0.0660 1.0000 0.0282
-9.500 -0.6099 0.05251 0.04841 -0.0764 0.9885 0.0247
-9.250 -0.5907 0.04749 0.04310 -0.0813 0.9814 0.0240
-9.000 -0.5749 0.04184 0.03699 -0.0858 0.9731 0.0236
-8.750 -0.5568 0.03748 0.03220 -0.0883 0.9640 0.0233
-8.500 -0.5325 0.03362 0.02782 -0.0906 0.9569 0.0235
-8.250 -0.5036 0.03066 0.02441 -0.0926 0.9501 0.0240
-8.000 -0.4757 0.02788 0.02131 -0.0939 0.9432 0.0250
-7.750 -0.4422 0.02631 0.01973 -0.0960 0.9372 0.0271
-7.500 -0.4028 0.02473 0.01794 -0.0988 0.9341 0.0299
-7.250 -0.3771 0.02274 0.01583 -0.0987 0.9245 0.0323
-7.000 -0.3392 0.02125 0.01434 -0.1012 0.9209 0.0366
-6.750 -0.3105 0.01988 0.01297 -0.1019 0.9121 0.0435
-6.500 -0.2724 0.01849 0.01156 -0.1044 0.9074 0.0546
-6.250 -0.2374 0.01740 0.01045 -0.1063 0.8996 0.0693
-6.000 -0.1972 0.01614 0.00924 -0.1094 0.8933 0.0905
-5.750 -0.1590 0.01501 0.00821 -0.1122 0.8848 0.1220
-5.500 -0.1189 0.01362 0.00712 -0.1157 0.8766 0.1910
-5.250 -0.0870 0.01243 0.00657 -0.1177 0.8643 0.3388
-5.000 -0.0505 0.01234 0.00652 -0.1193 0.8523 0.4083
-4.750 -0.0142 0.01243 0.00646 -0.1208 0.8402 0.4416
-4.500 0.0201 0.01256 0.00643 -0.1218 0.8278 0.4645
-4.250 0.0514 0.01272 0.00646 -0.1222 0.8149 0.4824
-4.000 0.0796 0.01287 0.00648 -0.1221 0.8015 0.4975
-3.750 0.1076 0.01300 0.00647 -0.1219 0.7890 0.5107
-3.500 0.1359 0.01311 0.00646 -0.1218 0.7773 0.5222
-3.250 0.1646 0.01320 0.00646 -0.1218 0.7666 0.5322
-3.000 0.1914 0.01329 0.00643 -0.1214 0.7554 0.5434
-2.750 0.2180 0.01344 0.00647 -0.1210 0.7449 0.5558
-2.500 0.2457 0.01353 0.00652 -0.1208 0.7359 0.5652
-2.250 0.2721 0.01356 0.00645 -0.1205 0.7259 0.5740
-2.000 0.2990 0.01360 0.00643 -0.1202 0.7169 0.5809
-1.750 0.3273 0.01362 0.00629 -0.1204 0.7088 0.5883
-1.500 0.3535 0.01363 0.00630 -0.1200 0.7003 0.5937
-1.250 0.3821 0.01367 0.00620 -0.1202 0.6929 0.6007
-1.000 0.4081 0.01368 0.00619 -0.1199 0.6848 0.6065
-0.750 0.4363 0.01372 0.00615 -0.1200 0.6780 0.6126
-0.500 0.4631 0.01377 0.00615 -0.1200 0.6710 0.6196
-0.250 0.4903 0.01380 0.00616 -0.1199 0.6644 0.6253
0.000 0.5182 0.01389 0.00617 -0.1200 0.6582 0.6324
0.250 0.5444 0.01392 0.00622 -0.1197 0.6513 0.6386
0.500 0.5735 0.01401 0.00623 -0.1201 0.6462 0.6459
0.750 0.5989 0.01408 0.00634 -0.1197 0.6399 0.6527
1.000 0.6262 0.01415 0.00641 -0.1197 0.6342 0.6603
1.250 0.6549 0.01427 0.00647 -0.1199 0.6293 0.6681
1.500 0.6796 0.01435 0.00663 -0.1194 0.6232 0.6761
1.750 0.7074 0.01444 0.00672 -0.1195 0.6183 0.6847
2.000 0.7358 0.01459 0.00685 -0.1198 0.6139 0.6945
2.250 0.7598 0.01467 0.00705 -0.1191 0.6081 0.7034
2.500 0.7872 0.01478 0.00716 -0.1191 0.6032 0.7143
2.750 0.8163 0.01494 0.00732 -0.1195 0.5993 0.7263
3.000 0.8390 0.01505 0.00759 -0.1186 0.5940 0.7382
3.250 0.8648 0.01516 0.00777 -0.1183 0.5891 0.7518
3.500 0.8931 0.01529 0.00793 -0.1184 0.5852 0.7676
3.750 0.9159 0.01544 0.00823 -0.1175 0.5804 0.7858
4.000 0.9389 0.01555 0.00848 -0.1166 0.5756 0.8067
4.250 0.9637 0.01562 0.00864 -0.1159 0.5715 0.8327
4.500 0.9862 0.01572 0.00886 -0.1147 0.5676 0.8687
4.750 1.0099 0.01572 0.00911 -0.1138 0.5624 0.9424
5.000 1.0459 0.01592 0.00931 -0.1160 0.5576 1.0000
5.250 1.0789 0.01621 0.00951 -0.1173 0.5537 1.0000
5.500 1.0999 0.01649 0.00992 -0.1163 0.5478 1.0000
5.750 1.1268 0.01669 0.01013 -0.1164 0.5423 1.0000
6.000 1.1558 0.01693 0.01033 -0.1168 0.5372 1.0000
6.250 1.1765 0.01715 0.01067 -0.1156 0.5304 1.0000
6.500 1.2061 0.01723 0.01070 -0.1159 0.5241 1.0000
6.750 1.2248 0.01739 0.01098 -0.1143 0.5159 1.0000
7.000 1.2532 0.01744 0.01096 -0.1144 0.5088 1.0000
7.250 1.2712 0.01763 0.01130 -0.1127 0.5010 1.0000
7.500 1.2980 0.01771 0.01136 -0.1125 0.4940 1.0000
7.750 1.3157 0.01790 0.01169 -0.1107 0.4860 1.0000
8.000 1.3412 0.01797 0.01174 -0.1103 0.4784 1.0000
8.250 1.3568 0.01814 0.01207 -0.1080 0.4695 1.0000
8.500 1.3786 0.01823 0.01219 -0.1069 0.4610 1.0000
8.750 1.3934 0.01835 0.01242 -0.1045 0.4509 1.0000
9.000 1.4077 0.01848 0.01266 -0.1020 0.4401 1.0000
9.250 1.4212 0.01861 0.01284 -0.0994 0.4286 1.0000
9.500 1.4313 0.01876 0.01303 -0.0962 0.4160 1.0000
9.750 1.4377 0.01900 0.01332 -0.0923 0.4022 1.0000
10.000 1.4429 0.01935 0.01376 -0.0884 0.3863 1.0000
10.250 1.4465 0.01982 0.01429 -0.0844 0.3672 1.0000
10.500 1.4475 0.02050 0.01493 -0.0802 0.3449 1.0000
10.750 1.4447 0.02145 0.01583 -0.0758 0.3168 1.0000
11.000 1.4368 0.02283 0.01707 -0.0711 0.2861 1.0000
11.250 1.4245 0.02468 0.01876 -0.0665 0.2551 1.0000
11.750 1.3978 0.02946 0.02328 -0.0589 0.2027 1.0000
12.000 1.3851 0.03225 0.02598 -0.0560 0.1818 1.0000
12.250 1.3742 0.03516 0.02882 -0.0538 0.1630 1.0000
12.500 1.3641 0.03824 0.03185 -0.0520 0.1474 1.0000
12.750 1.3549 0.04142 0.03499 -0.0506 0.1336 1.0000
13.000 1.3473 0.04462 0.03817 -0.0495 0.1217 1.0000
13.250 1.3397 0.04793 0.04148 -0.0486 0.1113 1.0000
13.500 1.3308 0.05152 0.04503 -0.0479 0.1023 1.0000
13.750 1.3281 0.05460 0.04817 -0.0475 0.0929 1.0000
14.000 1.3231 0.05799 0.05157 -0.0471 0.0852 1.0000
14.250 1.3176 0.06154 0.05510 -0.0470 0.0783 1.0000
14.500 1.3162 0.06472 0.05836 -0.0469 0.0714 1.0000
14.750 1.3109 0.06840 0.06200 -0.0470 0.0659 1.0000
15.000 1.3110 0.07154 0.06525 -0.0472 0.0602 1.0000
15.250 1.3075 0.07519 0.06889 -0.0475 0.0554 1.0000
15.500 1.3067 0.07853 0.07231 -0.0478 0.0508 1.0000
15.750 1.3055 0.08206 0.07590 -0.0484 0.0465 1.0000
16.000 1.3026 0.08569 0.07954 -0.0488 0.0427 1.0000
16.250 1.3030 0.08916 0.08313 -0.0495 0.0391 1.0000
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Polar data table (+)
Polar graphs
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