EPPLER 855 AIRFOIL (e855-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 855 AIRFOIL (e855-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.64 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e855-il-1000000-n5.txt Download as CSV file: xf-e855-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7470 0.08305 0.08039 -0.0607 1.0000 0.0029
-15.250 -0.7750 0.07453 0.07173 -0.0650 1.0000 0.0029
-15.000 -0.8017 0.06680 0.06386 -0.0689 1.0000 0.0029
-14.750 -0.8209 0.06083 0.05777 -0.0717 1.0000 0.0029
-14.500 -0.8245 0.05663 0.05350 -0.0744 0.9997 0.0029
-14.250 -0.8317 0.05064 0.04735 -0.0801 0.9985 0.0029
-14.000 -0.8304 0.04594 0.04253 -0.0851 0.9969 0.0029
-13.750 -0.8278 0.04133 0.03778 -0.0904 0.9951 0.0029
-13.500 -0.8194 0.03772 0.03404 -0.0949 0.9937 0.0029
-13.250 -0.8222 0.03378 0.02996 -0.0979 0.9911 0.0029
-13.000 -0.8182 0.03025 0.02628 -0.1016 0.9882 0.0030
-12.750 -0.7990 0.02828 0.02423 -0.1047 0.9861 0.0029
-12.500 -0.7849 0.02513 0.02092 -0.1097 0.9838 0.0030
-12.250 -0.7874 0.02345 0.01915 -0.1086 0.9761 0.0031
-11.750 -0.7626 0.02081 0.01631 -0.1079 0.9627 0.0032
-11.500 -0.7515 0.01987 0.01530 -0.1062 0.9521 0.0032
-11.250 -0.7321 0.01891 0.01427 -0.1060 0.9434 0.0033
-11.000 -0.7044 0.01799 0.01327 -0.1072 0.9358 0.0034
-10.750 -0.6702 0.01706 0.01225 -0.1097 0.9283 0.0035
-10.500 -0.6255 0.01611 0.01120 -0.1143 0.9213 0.0036
-10.250 -0.5694 0.01515 0.01013 -0.1214 0.9119 0.0038
-10.000 -0.5132 0.01436 0.00920 -0.1283 0.8955 0.0039
-9.750 -0.4781 0.01386 0.00851 -0.1306 0.8653 0.0041
-9.500 -0.4559 0.01354 0.00801 -0.1300 0.8371 0.0043
-9.250 -0.4357 0.01325 0.00757 -0.1289 0.8138 0.0044
-9.000 -0.4154 0.01289 0.00708 -0.1278 0.7945 0.0047
-8.750 -0.3941 0.01258 0.00667 -0.1269 0.7776 0.0048
-8.500 -0.3724 0.01227 0.00627 -0.1260 0.7615 0.0053
-8.250 -0.3497 0.01201 0.00592 -0.1253 0.7469 0.0058
-8.000 -0.3265 0.01177 0.00558 -0.1246 0.7322 0.0062
-7.750 -0.3031 0.01152 0.00525 -0.1240 0.7191 0.0069
-7.250 -0.2546 0.01103 0.00465 -0.1230 0.6958 0.0097
-7.000 -0.2298 0.01083 0.00438 -0.1226 0.6846 0.0115
-6.750 -0.2050 0.01062 0.00412 -0.1222 0.6735 0.0144
-6.500 -0.1798 0.01042 0.00388 -0.1218 0.6631 0.0176
-6.250 -0.1541 0.01021 0.00365 -0.1216 0.6542 0.0224
-6.000 -0.1286 0.01002 0.00344 -0.1213 0.6450 0.0282
-5.750 -0.1025 0.00983 0.00324 -0.1211 0.6362 0.0349
-5.500 -0.0766 0.00966 0.00305 -0.1209 0.6275 0.0432
-5.250 -0.0505 0.00945 0.00287 -0.1208 0.6190 0.0559
-5.000 -0.0242 0.00926 0.00270 -0.1206 0.6119 0.0717
-4.750 0.0023 0.00908 0.00254 -0.1205 0.6041 0.0877
-4.500 0.0287 0.00890 0.00239 -0.1204 0.5971 0.1073
-4.250 0.0554 0.00870 0.00224 -0.1203 0.5897 0.1325
-4.000 0.0816 0.00847 0.00208 -0.1202 0.5833 0.1679
-3.750 0.1083 0.00819 0.00193 -0.1203 0.5773 0.2117
-3.500 0.1346 0.00792 0.00179 -0.1202 0.5709 0.2630
-3.250 0.1615 0.00772 0.00170 -0.1202 0.5651 0.3077
-3.000 0.1885 0.00755 0.00163 -0.1202 0.5591 0.3509
-2.750 0.2157 0.00750 0.00160 -0.1202 0.5536 0.3764
-2.500 0.2437 0.00746 0.00158 -0.1202 0.5489 0.3921
-2.250 0.2714 0.00746 0.00156 -0.1202 0.5436 0.4034
-2.000 0.2989 0.00748 0.00156 -0.1202 0.5384 0.4141
-1.750 0.3269 0.00747 0.00155 -0.1202 0.5336 0.4255
-1.500 0.3546 0.00748 0.00156 -0.1202 0.5288 0.4391
-1.250 0.3821 0.00751 0.00158 -0.1202 0.5243 0.4497
-1.000 0.4100 0.00753 0.00159 -0.1202 0.5205 0.4574
-0.500 0.4655 0.00759 0.00161 -0.1202 0.5116 0.4661
-0.250 0.4929 0.00763 0.00163 -0.1202 0.5074 0.4704
0.000 0.5209 0.00766 0.00165 -0.1202 0.5039 0.4748
0.250 0.5486 0.00770 0.00168 -0.1202 0.5001 0.4783
0.500 0.5760 0.00774 0.00171 -0.1202 0.4962 0.4827
0.750 0.6032 0.00779 0.00175 -0.1201 0.4924 0.4870
1.000 0.6310 0.00783 0.00179 -0.1201 0.4889 0.4911
1.250 0.6586 0.00787 0.00184 -0.1201 0.4854 0.4950
1.500 0.6858 0.00792 0.00189 -0.1200 0.4819 0.4998
1.750 0.7127 0.00799 0.00195 -0.1199 0.4783 0.5044
2.000 0.7402 0.00803 0.00201 -0.1198 0.4751 0.5085
2.250 0.7675 0.00807 0.00207 -0.1198 0.4716 0.5134
2.500 0.7946 0.00813 0.00215 -0.1197 0.4683 0.5188
2.750 0.8213 0.00820 0.00222 -0.1196 0.4648 0.5235
3.000 0.8481 0.00827 0.00231 -0.1194 0.4616 0.5286
3.250 0.8753 0.00831 0.00239 -0.1193 0.4584 0.5348
3.750 0.9285 0.00845 0.00257 -0.1190 0.4511 0.5463
4.000 0.9545 0.00855 0.00268 -0.1187 0.4472 0.5529
4.250 0.9812 0.00860 0.00278 -0.1186 0.4421 0.5597
4.500 1.0068 0.00870 0.00289 -0.1182 0.4355 0.5674
4.750 1.0325 0.00880 0.00301 -0.1179 0.4294 0.5745
5.000 1.0577 0.00890 0.00313 -0.1175 0.4209 0.5826
5.250 1.0824 0.00903 0.00326 -0.1170 0.4110 0.5914
5.500 1.1064 0.00918 0.00341 -0.1164 0.4015 0.6013
5.750 1.1312 0.00929 0.00357 -0.1159 0.3927 0.6114
6.000 1.1547 0.00944 0.00373 -0.1151 0.3836 0.6218
6.250 1.1769 0.00962 0.00391 -0.1142 0.3729 0.6332
6.500 1.1994 0.00978 0.00410 -0.1133 0.3616 0.6464
6.750 1.2204 0.00999 0.00431 -0.1121 0.3475 0.6612
7.000 1.2399 0.01027 0.00457 -0.1106 0.3304 0.6771
7.250 1.2572 0.01064 0.00489 -0.1088 0.3067 0.6942
7.500 1.2712 0.01115 0.00532 -0.1064 0.2767 0.7130
7.750 1.2803 0.01188 0.00589 -0.1032 0.2380 0.7361
8.000 1.2903 0.01251 0.00645 -0.1002 0.2074 0.7660
8.250 1.3000 0.01307 0.00700 -0.0971 0.1825 0.8089
8.500 1.3081 0.01334 0.00749 -0.0935 0.1630 0.9447
8.750 1.3206 0.01401 0.00807 -0.0912 0.1421 1.0000
9.000 1.3323 0.01464 0.00863 -0.0887 0.1256 1.0000
9.250 1.3429 0.01531 0.00923 -0.0861 0.1107 1.0000
9.500 1.3533 0.01600 0.00987 -0.0836 0.0977 1.0000
9.750 1.3624 0.01676 0.01057 -0.0809 0.0852 1.0000
10.000 1.3706 0.01758 0.01135 -0.0783 0.0737 1.0000
10.250 1.3787 0.01844 0.01217 -0.0757 0.0646 1.0000
10.500 1.3843 0.01946 0.01316 -0.0730 0.0542 1.0000
10.750 1.3931 0.02038 0.01408 -0.0708 0.0478 1.0000
11.000 1.3988 0.02152 0.01520 -0.0684 0.0406 1.0000
11.250 1.4033 0.02279 0.01646 -0.0660 0.0341 1.0000
11.500 1.4088 0.02410 0.01776 -0.0640 0.0289 1.0000
11.750 1.4160 0.02536 0.01905 -0.0623 0.0262 1.0000
12.000 1.4218 0.02679 0.02050 -0.0606 0.0231 1.0000
12.250 1.4271 0.02832 0.02205 -0.0590 0.0203 1.0000
12.500 1.4329 0.02990 0.02367 -0.0576 0.0182 1.0000
12.750 1.4371 0.03166 0.02547 -0.0563 0.0162 1.0000
13.000 1.4425 0.03341 0.02726 -0.0552 0.0144 1.0000
13.250 1.4446 0.03551 0.02939 -0.0540 0.0122 1.0000
13.500 1.4495 0.03743 0.03136 -0.0532 0.0110 1.0000
13.750 1.4517 0.03965 0.03361 -0.0523 0.0095 1.0000
14.000 1.4546 0.04188 0.03589 -0.0516 0.0081 1.0000
14.250 1.4566 0.04426 0.03832 -0.0510 0.0071 1.0000
14.500 1.4594 0.04663 0.04075 -0.0505 0.0063 1.0000
14.750 1.4613 0.04914 0.04331 -0.0501 0.0054 1.0000
15.000 1.4626 0.05178 0.04601 -0.0498 0.0047 1.0000
15.250 1.4653 0.05435 0.04864 -0.0496 0.0044 1.0000
15.500 1.4659 0.05721 0.05156 -0.0495 0.0037 1.0000
15.750 1.4677 0.05997 0.05439 -0.0496 0.0035 1.0000
16.000 1.4689 0.06286 0.05734 -0.0497 0.0030 1.0000
16.250 1.4710 0.06569 0.06024 -0.0499 0.0029 1.0000
16.500 1.4698 0.06902 0.06363 -0.0502 0.0024 1.0000
16.750 1.4714 0.07204 0.06672 -0.0506 0.0023 1.0000
17.000 1.4716 0.07526 0.07002 -0.0511 0.0021 1.0000
17.250 1.4725 0.07847 0.07330 -0.0516 0.0020 1.0000
17.500 1.4722 0.08188 0.07679 -0.0523 0.0019 1.0000
17.750 1.4707 0.08553 0.08051 -0.0531 0.0016 1.0000
18.000 1.4702 0.08907 0.08413 -0.0540 0.0015 1.0000
18.250 1.4693 0.09271 0.08785 -0.0550 0.0015 1.0000
18.500 1.4663 0.09674 0.09196 -0.0561 0.0014 1.0000
18.750 1.4653 0.10050 0.09580 -0.0573 0.0013 1.0000
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Polar data table (+)
Polar graphs
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