EPPLER 855 AIRFOIL (e855-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 855 AIRFOIL (e855-il) Reynolds number: 1,000,000 Max Cl/Cd: 140.47 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e855-il-1000000.txt Download as CSV file: xf-e855-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.5956 0.09678 0.09482 -0.0523 1.0000 0.0057
-14.250 -0.6561 0.08028 0.07808 -0.0611 1.0000 0.0055
-14.000 -0.6901 0.07051 0.06813 -0.0665 1.0000 0.0054
-13.750 -0.7156 0.06331 0.06078 -0.0702 1.0000 0.0053
-13.500 -0.7381 0.05727 0.05461 -0.0730 1.0000 0.0053
-13.250 -0.7557 0.05241 0.04964 -0.0749 1.0000 0.0053
-13.000 -0.7808 0.04713 0.04419 -0.0763 1.0000 0.0053
-12.750 -0.7911 0.04396 0.04093 -0.0767 1.0000 0.0053
-12.500 -0.7954 0.03975 0.03658 -0.0801 0.9989 0.0053
-12.250 -0.7835 0.03592 0.03256 -0.0858 0.9962 0.0053
-12.000 -0.7683 0.03236 0.02883 -0.0916 0.9940 0.0053
-11.750 -0.7560 0.02951 0.02582 -0.0954 0.9893 0.0054
-11.500 -0.7383 0.02688 0.02302 -0.1000 0.9854 0.0054
-11.250 -0.7175 0.02478 0.02076 -0.1028 0.9820 0.0054
-11.000 -0.6980 0.02314 0.01899 -0.1038 0.9766 0.0055
-10.750 -0.6704 0.02161 0.01733 -0.1060 0.9740 0.0056
-10.500 -0.6400 0.02025 0.01585 -0.1085 0.9724 0.0057
-10.250 -0.6251 0.01927 0.01480 -0.1071 0.9640 0.0058
-10.000 -0.5947 0.01834 0.01379 -0.1088 0.9612 0.0059
-9.750 -0.5779 0.01736 0.01273 -0.1075 0.9518 0.0060
-9.500 -0.5516 0.01646 0.01174 -0.1081 0.9460 0.0062
-9.250 -0.5275 0.01565 0.01085 -0.1081 0.9370 0.0063
-9.000 -0.4954 0.01472 0.00982 -0.1097 0.9304 0.0064
-8.750 -0.4588 0.01345 0.00843 -0.1127 0.9230 0.0067
-8.500 -0.4128 0.01254 0.00743 -0.1173 0.9156 0.0073
-8.250 -0.3583 0.01189 0.00670 -0.1236 0.9061 0.0081
-8.000 -0.3135 0.01133 0.00599 -0.1277 0.8869 0.0090
-7.750 -0.2825 0.01091 0.00544 -0.1288 0.8627 0.0103
-7.500 -0.2575 0.01061 0.00501 -0.1285 0.8403 0.0124
-7.250 -0.2346 0.01031 0.00462 -0.1277 0.8195 0.0164
-7.000 -0.2116 0.01006 0.00430 -0.1269 0.8005 0.0217
-6.750 -0.1882 0.00985 0.00403 -0.1262 0.7833 0.0275
-6.500 -0.1642 0.00968 0.00380 -0.1256 0.7676 0.0336
-6.000 -0.1153 0.00930 0.00336 -0.1246 0.7393 0.0504
-5.750 -0.0905 0.00909 0.00314 -0.1241 0.7262 0.0640
-5.500 -0.0655 0.00887 0.00294 -0.1237 0.7136 0.0820
-5.250 -0.0405 0.00864 0.00275 -0.1234 0.7020 0.1055
-5.000 -0.0156 0.00837 0.00255 -0.1230 0.6910 0.1378
-4.750 0.0096 0.00804 0.00233 -0.1228 0.6801 0.1825
-4.500 0.0344 0.00763 0.00211 -0.1226 0.6700 0.2489
-4.250 0.0592 0.00727 0.00195 -0.1223 0.6601 0.3212
-4.000 0.0859 0.00711 0.00187 -0.1222 0.6508 0.3634
-3.750 0.1128 0.00707 0.00183 -0.1221 0.6422 0.3883
-3.500 0.1400 0.00705 0.00179 -0.1219 0.6333 0.4050
-3.250 0.1676 0.00706 0.00176 -0.1219 0.6252 0.4176
-2.750 0.2225 0.00709 0.00174 -0.1217 0.6099 0.4413
-2.500 0.2500 0.00713 0.00172 -0.1216 0.6027 0.4491
-2.250 0.2777 0.00715 0.00171 -0.1216 0.5960 0.4563
-2.000 0.3054 0.00720 0.00170 -0.1216 0.5891 0.4628
-1.750 0.3327 0.00723 0.00171 -0.1215 0.5827 0.4707
-1.500 0.3606 0.00726 0.00172 -0.1215 0.5767 0.4796
-1.250 0.3879 0.00731 0.00174 -0.1214 0.5708 0.4877
-1.000 0.4158 0.00736 0.00175 -0.1214 0.5656 0.4936
-0.750 0.4434 0.00736 0.00176 -0.1214 0.5599 0.4987
-0.500 0.4705 0.00743 0.00178 -0.1213 0.5545 0.5034
-0.250 0.4986 0.00746 0.00180 -0.1213 0.5498 0.5077
0.000 0.5262 0.00748 0.00181 -0.1213 0.5449 0.5124
0.250 0.5532 0.00754 0.00185 -0.1212 0.5401 0.5170
0.500 0.5810 0.00758 0.00188 -0.1212 0.5359 0.5218
0.750 0.6087 0.00761 0.00191 -0.1212 0.5313 0.5264
1.000 0.6358 0.00766 0.00196 -0.1211 0.5268 0.5314
1.250 0.6629 0.00773 0.00202 -0.1210 0.5227 0.5366
1.500 0.6908 0.00776 0.00206 -0.1211 0.5190 0.5418
1.750 0.7181 0.00779 0.00212 -0.1210 0.5149 0.5475
2.000 0.7450 0.00787 0.00219 -0.1209 0.5107 0.5532
2.250 0.7720 0.00794 0.00226 -0.1208 0.5069 0.5591
2.500 0.7996 0.00797 0.00233 -0.1208 0.5035 0.5659
2.750 0.8267 0.00802 0.00240 -0.1207 0.4997 0.5725
3.000 0.8532 0.00809 0.00249 -0.1205 0.4958 0.5798
3.500 0.9072 0.00821 0.00268 -0.1203 0.4886 0.5964
3.750 0.9340 0.00827 0.00277 -0.1202 0.4848 0.6054
4.000 0.9601 0.00835 0.00288 -0.1199 0.4807 0.6155
4.250 0.9862 0.00843 0.00299 -0.1197 0.4759 0.6264
4.500 1.0128 0.00846 0.00309 -0.1195 0.4709 0.6384
4.750 1.0382 0.00854 0.00320 -0.1191 0.4656 0.6515
5.000 1.0638 0.00862 0.00332 -0.1188 0.4598 0.6658
5.250 1.0893 0.00866 0.00343 -0.1184 0.4529 0.6824
5.500 1.1136 0.00877 0.00358 -0.1178 0.4468 0.7011
5.750 1.1395 0.00879 0.00370 -0.1175 0.4414 0.7225
6.000 1.1637 0.00887 0.00385 -0.1169 0.4352 0.7465
6.250 1.1880 0.00893 0.00401 -0.1163 0.4294 0.7755
6.500 1.2111 0.00896 0.00417 -0.1154 0.4230 0.8144
6.750 1.2291 0.00895 0.00434 -0.1134 0.4163 0.8823
7.000 1.2544 0.00893 0.00447 -0.1129 0.4085 1.0000
7.250 1.2768 0.00911 0.00464 -0.1120 0.3999 1.0000
7.500 1.2979 0.00934 0.00483 -0.1108 0.3881 1.0000
7.750 1.3190 0.00957 0.00504 -0.1097 0.3744 1.0000
8.000 1.3391 0.00984 0.00527 -0.1084 0.3599 1.0000
8.250 1.3578 0.01017 0.00555 -0.1068 0.3422 1.0000
8.500 1.3738 0.01063 0.00591 -0.1048 0.3169 1.0000
8.750 1.3846 0.01129 0.00640 -0.1019 0.2831 1.0000
9.000 1.3907 0.01216 0.00704 -0.0983 0.2436 1.0000
9.250 1.3964 0.01304 0.00774 -0.0947 0.2095 1.0000
9.500 1.4013 0.01394 0.00847 -0.0911 0.1787 1.0000
9.750 1.4059 0.01486 0.00924 -0.0875 0.1525 1.0000
10.250 1.4164 0.01669 0.01088 -0.0809 0.1131 1.0000
10.500 1.4213 0.01767 0.01178 -0.0778 0.0973 1.0000
10.750 1.4268 0.01866 0.01273 -0.0750 0.0848 1.0000
11.000 1.4320 0.01973 0.01376 -0.0723 0.0742 1.0000
11.250 1.4362 0.02091 0.01490 -0.0696 0.0644 1.0000
11.500 1.4414 0.02212 0.01609 -0.0672 0.0569 1.0000
11.750 1.4479 0.02331 0.01730 -0.0652 0.0513 1.0000
12.000 1.4512 0.02479 0.01877 -0.0630 0.0451 1.0000
12.250 1.4567 0.02621 0.02021 -0.0613 0.0402 1.0000
12.500 1.4590 0.02793 0.02194 -0.0594 0.0354 1.0000
12.750 1.4646 0.02950 0.02355 -0.0580 0.0321 1.0000
13.000 1.4665 0.03144 0.02550 -0.0565 0.0284 1.0000
13.250 1.4701 0.03332 0.02742 -0.0553 0.0253 1.0000
13.500 1.4722 0.03541 0.02953 -0.0541 0.0228 1.0000
13.750 1.4750 0.03752 0.03168 -0.0532 0.0205 1.0000
14.000 1.4770 0.03976 0.03396 -0.0523 0.0183 1.0000
14.250 1.4776 0.04221 0.03644 -0.0515 0.0162 1.0000
14.500 1.4807 0.04449 0.03878 -0.0509 0.0148 1.0000
14.750 1.4803 0.04718 0.04151 -0.0504 0.0129 1.0000
15.000 1.4817 0.04975 0.04414 -0.0500 0.0113 1.0000
15.250 1.4817 0.05255 0.04699 -0.0497 0.0101 1.0000
15.500 1.4816 0.05545 0.04993 -0.0496 0.0087 1.0000
15.750 1.4818 0.05836 0.05291 -0.0495 0.0078 1.0000
16.000 1.4794 0.06163 0.05623 -0.0496 0.0064 1.0000
16.250 1.4796 0.06469 0.05936 -0.0497 0.0059 1.0000
16.500 1.4748 0.06844 0.06316 -0.0500 0.0048 1.0000
16.750 1.4752 0.07160 0.06640 -0.0504 0.0045 1.0000
17.000 1.4725 0.07522 0.07008 -0.0509 0.0039 1.0000
17.250 1.4706 0.07880 0.07374 -0.0516 0.0037 1.0000
17.500 1.4662 0.08282 0.07785 -0.0524 0.0034 1.0000
17.750 1.4647 0.08651 0.08164 -0.0532 0.0031 1.0000
18.000 1.4640 0.09009 0.08530 -0.0541 0.0029 1.0000
18.250 1.4620 0.09394 0.08923 -0.0552 0.0029 1.0000
18.500 1.4581 0.09814 0.09352 -0.0564 0.0027 1.0000
18.750 1.4544 0.10235 0.09782 -0.0577 0.0026 1.0000
19.000 1.4498 0.10678 0.10233 -0.0593 0.0025 1.0000
19.250 1.4424 0.11171 0.10736 -0.0611 0.0024 1.0000
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Polar data table (+)
Polar graphs
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