EPPLER 855 AIRFOIL (e855-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 855 AIRFOIL (e855-il) Reynolds number: 500,000 Max Cl/Cd: 106.9 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e855-il-500000-n5.txt Download as CSV file: xf-e855-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.5736 0.10840 0.10572 -0.0492 1.0000 0.0050
-14.750 -0.6345 0.09138 0.08843 -0.0574 1.0000 0.0048
-14.500 -0.6607 0.08236 0.07923 -0.0619 1.0000 0.0047
-14.250 -0.6852 0.07432 0.07105 -0.0660 1.0000 0.0047
-14.000 -0.7055 0.06763 0.06424 -0.0693 1.0000 0.0047
-13.750 -0.7190 0.06257 0.05906 -0.0716 1.0000 0.0046
-13.500 -0.7362 0.05742 0.05379 -0.0737 1.0000 0.0047
-13.250 -0.7527 0.05274 0.04900 -0.0753 1.0000 0.0047
-13.000 -0.7668 0.04870 0.04485 -0.0763 1.0000 0.0047
-12.750 -0.7697 0.04535 0.04137 -0.0781 0.9994 0.0046
-12.500 -0.7658 0.04083 0.03668 -0.0834 0.9968 0.0047
-12.250 -0.7547 0.03734 0.03304 -0.0882 0.9942 0.0047
-12.000 -0.7451 0.03421 0.02977 -0.0918 0.9904 0.0048
-11.750 -0.7310 0.03140 0.02683 -0.0958 0.9863 0.0049
-11.500 -0.7176 0.02889 0.02418 -0.0991 0.9816 0.0049
-11.000 -0.6960 0.02529 0.02034 -0.1007 0.9647 0.0051
-10.750 -0.6818 0.02386 0.01880 -0.1006 0.9552 0.0051
-10.500 -0.6626 0.02262 0.01746 -0.1008 0.9464 0.0053
-10.250 -0.6441 0.02146 0.01617 -0.1006 0.9365 0.0054
-10.000 -0.6200 0.02037 0.01498 -0.1013 0.9282 0.0055
-9.750 -0.5899 0.01926 0.01375 -0.1031 0.9212 0.0057
-9.500 -0.5571 0.01825 0.01262 -0.1052 0.9129 0.0060
-9.250 -0.5159 0.01724 0.01148 -0.1090 0.9057 0.0063
-9.000 -0.4713 0.01617 0.01028 -0.1137 0.8958 0.0068
-8.750 -0.4216 0.01534 0.00934 -0.1192 0.8845 0.0073
-8.500 -0.3787 0.01469 0.00854 -0.1231 0.8673 0.0082
-8.250 -0.3450 0.01417 0.00785 -0.1249 0.8461 0.0090
-8.000 -0.3184 0.01375 0.00730 -0.1252 0.8260 0.0101
-7.750 -0.2938 0.01343 0.00683 -0.1249 0.8075 0.0115
-7.500 -0.2705 0.01308 0.00640 -0.1244 0.7908 0.0138
-7.250 -0.2473 0.01276 0.00601 -0.1238 0.7748 0.0172
-7.000 -0.2238 0.01248 0.00564 -0.1232 0.7598 0.0209
-6.750 -0.2000 0.01223 0.00531 -0.1226 0.7457 0.0254
-6.500 -0.1759 0.01200 0.00501 -0.1221 0.7329 0.0306
-6.250 -0.1518 0.01175 0.00471 -0.1216 0.7211 0.0376
-6.000 -0.1274 0.01149 0.00444 -0.1212 0.7092 0.0475
-5.750 -0.1027 0.01125 0.00417 -0.1208 0.6977 0.0594
-5.500 -0.0778 0.01102 0.00392 -0.1205 0.6872 0.0733
-5.250 -0.0528 0.01079 0.00369 -0.1201 0.6770 0.0896
-5.000 -0.0273 0.01053 0.00346 -0.1199 0.6676 0.1111
-4.750 -0.0021 0.01027 0.00323 -0.1196 0.6585 0.1388
-4.500 0.0231 0.00995 0.00300 -0.1194 0.6491 0.1783
-4.250 0.0481 0.00956 0.00276 -0.1192 0.6408 0.2346
-4.000 0.0734 0.00922 0.00258 -0.1191 0.6327 0.2967
-3.750 0.0997 0.00903 0.00247 -0.1190 0.6253 0.3414
-3.500 0.1263 0.00894 0.00242 -0.1188 0.6174 0.3745
-3.250 0.1533 0.00891 0.00238 -0.1187 0.6102 0.3986
-3.000 0.1804 0.00891 0.00234 -0.1186 0.6029 0.4138
-2.750 0.2077 0.00892 0.00231 -0.1185 0.5968 0.4251
-2.500 0.2352 0.00893 0.00228 -0.1184 0.5903 0.4350
-2.250 0.2622 0.00898 0.00226 -0.1182 0.5841 0.4460
-2.000 0.2898 0.00899 0.00227 -0.1182 0.5778 0.4594
-1.750 0.3169 0.00902 0.00228 -0.1181 0.5720 0.4700
-1.500 0.3444 0.00907 0.00226 -0.1180 0.5670 0.4772
-1.250 0.3719 0.00908 0.00227 -0.1179 0.5615 0.4821
-1.000 0.3990 0.00912 0.00226 -0.1178 0.5561 0.4868
-0.750 0.4264 0.00917 0.00227 -0.1178 0.5512 0.4915
-0.500 0.4539 0.00920 0.00228 -0.1177 0.5461 0.4957
-0.250 0.4810 0.00924 0.00230 -0.1176 0.5415 0.5003
0.000 0.5082 0.00930 0.00233 -0.1175 0.5373 0.5052
0.250 0.5358 0.00934 0.00235 -0.1175 0.5327 0.5095
0.500 0.5629 0.00938 0.00239 -0.1174 0.5280 0.5139
0.750 0.5896 0.00945 0.00244 -0.1172 0.5238 0.5191
1.000 0.6172 0.00950 0.00249 -0.1172 0.5200 0.5240
1.250 0.6444 0.00954 0.00255 -0.1171 0.5160 0.5286
1.500 0.6713 0.00960 0.00261 -0.1170 0.5118 0.5340
1.750 0.6978 0.00970 0.00268 -0.1168 0.5079 0.5396
2.000 0.7251 0.00973 0.00277 -0.1167 0.5041 0.5448
2.250 0.7521 0.00979 0.00285 -0.1166 0.5004 0.5508
2.500 0.7788 0.00987 0.00294 -0.1165 0.4967 0.5570
2.750 0.8050 0.00997 0.00305 -0.1162 0.4931 0.5633
3.000 0.8321 0.01003 0.00315 -0.1162 0.4895 0.5700
3.250 0.8588 0.01009 0.00326 -0.1160 0.4858 0.5768
3.500 0.8851 0.01018 0.00338 -0.1158 0.4822 0.5849
3.750 0.9110 0.01028 0.00351 -0.1155 0.4786 0.5926
4.000 0.9375 0.01036 0.00364 -0.1153 0.4752 0.6011
4.250 0.9638 0.01043 0.00379 -0.1151 0.4715 0.6099
4.500 0.9896 0.01052 0.00393 -0.1148 0.4676 0.6201
4.750 1.0147 0.01064 0.00408 -0.1144 0.4636 0.6311
5.000 1.0402 0.01072 0.00424 -0.1140 0.4586 0.6422
5.250 1.0648 0.01081 0.00440 -0.1135 0.4523 0.6543
5.500 1.0886 0.01093 0.00457 -0.1128 0.4464 0.6681
5.750 1.1125 0.01101 0.00474 -0.1121 0.4381 0.6839
6.000 1.1350 0.01114 0.00492 -0.1112 0.4294 0.7014
6.250 1.1574 0.01125 0.00510 -0.1102 0.4206 0.7208
6.750 1.1994 0.01148 0.00552 -0.1077 0.4041 0.7707
7.000 1.2190 0.01156 0.00574 -0.1062 0.3947 0.8082
7.250 1.2339 0.01162 0.00597 -0.1036 0.3862 0.8720
7.500 1.2561 0.01175 0.00620 -0.1026 0.3740 1.0000
7.750 1.2744 0.01207 0.00649 -0.1010 0.3589 1.0000
8.000 1.2918 0.01243 0.00682 -0.0993 0.3417 1.0000
8.250 1.3058 0.01292 0.00722 -0.0970 0.3178 1.0000
8.500 1.3145 0.01365 0.00778 -0.0939 0.2852 1.0000
8.750 1.3203 0.01454 0.00848 -0.0904 0.2496 1.0000
9.000 1.3257 0.01547 0.00927 -0.0870 0.2191 1.0000
9.250 1.3313 0.01641 0.01009 -0.0837 0.1934 1.0000
9.500 1.3372 0.01735 0.01094 -0.0806 0.1717 1.0000
9.750 1.3430 0.01834 0.01184 -0.0776 0.1524 1.0000
10.000 1.3478 0.01940 0.01284 -0.0747 0.1343 1.0000
10.250 1.3528 0.02051 0.01390 -0.0720 0.1195 1.0000
10.500 1.3570 0.02172 0.01507 -0.0693 0.1061 1.0000
10.750 1.3617 0.02298 0.01631 -0.0669 0.0949 1.0000
11.000 1.3658 0.02435 0.01767 -0.0647 0.0849 1.0000
11.250 1.3692 0.02585 0.01916 -0.0626 0.0762 1.0000
11.500 1.3740 0.02735 0.02068 -0.0608 0.0684 1.0000
11.750 1.3777 0.02901 0.02236 -0.0591 0.0618 1.0000
12.000 1.3802 0.03086 0.02420 -0.0575 0.0551 1.0000
12.250 1.3828 0.03277 0.02614 -0.0561 0.0486 1.0000
12.500 1.3843 0.03489 0.02826 -0.0549 0.0434 1.0000
12.750 1.3867 0.03700 0.03040 -0.0538 0.0381 1.0000
13.000 1.3866 0.03942 0.03284 -0.0528 0.0327 1.0000
13.250 1.3879 0.04178 0.03523 -0.0520 0.0289 1.0000
13.500 1.3897 0.04417 0.03767 -0.0513 0.0261 1.0000
13.750 1.3912 0.04666 0.04020 -0.0508 0.0233 1.0000
14.000 1.3918 0.04930 0.04289 -0.0503 0.0207 1.0000
14.250 1.3941 0.05184 0.04549 -0.0500 0.0188 1.0000
14.500 1.3955 0.05453 0.04824 -0.0498 0.0173 1.0000
14.750 1.3965 0.05734 0.05111 -0.0497 0.0156 1.0000
15.000 1.3981 0.06012 0.05395 -0.0497 0.0140 1.0000
15.250 1.3987 0.06307 0.05696 -0.0498 0.0128 1.0000
15.500 1.3999 0.06603 0.06000 -0.0499 0.0117 1.0000
15.750 1.4009 0.06907 0.06312 -0.0502 0.0107 1.0000
16.000 1.4002 0.07238 0.06648 -0.0506 0.0095 1.0000
16.250 1.4013 0.07550 0.06968 -0.0510 0.0089 1.0000
16.500 1.4013 0.07882 0.07308 -0.0515 0.0078 1.0000
16.750 1.4010 0.08226 0.07660 -0.0522 0.0073 1.0000
17.000 1.3999 0.08584 0.08026 -0.0529 0.0065 1.0000
17.250 1.3999 0.08933 0.08383 -0.0537 0.0061 1.0000
17.500 1.3982 0.09309 0.08767 -0.0547 0.0055 1.0000
17.750 1.3955 0.09709 0.09175 -0.0558 0.0049 1.0000
18.000 1.3949 0.10081 0.09556 -0.0569 0.0045 1.0000
18.250 1.3934 0.10470 0.09955 -0.0582 0.0043 1.0000
18.500 1.3906 0.10883 0.10377 -0.0596 0.0039 1.0000
18.750 1.3873 0.11308 0.10811 -0.0611 0.0036 1.0000
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Polar data table (+)
Polar graphs
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