EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E853 AIRFOIL (e853-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.37 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e853-il-1000000-n5.txt Download as CSV file: xf-e853-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E853 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4329 0.08877 0.08716 -0.0501 0.9976 0.0023
-10.250 -0.4477 0.07835 0.07676 -0.0575 0.9960 0.0022
-10.000 -0.5286 0.04702 0.04527 -0.0817 0.9911 0.0021
-9.500 -0.5587 0.03064 0.02813 -0.0990 0.9683 0.0020
-9.250 -0.5542 0.02628 0.02336 -0.1001 0.9548 0.0020
-9.000 -0.5345 0.02200 0.01858 -0.1028 0.9454 0.0019
-8.750 -0.5016 0.01909 0.01527 -0.1065 0.9385 0.0019
-8.500 -0.4614 0.01694 0.01279 -0.1110 0.9312 0.0019
-8.000 -0.3947 0.01409 0.00937 -0.1155 0.8977 0.0020
-7.750 -0.3696 0.01329 0.00835 -0.1156 0.8780 0.0020
-7.500 -0.3463 0.01253 0.00739 -0.1152 0.8600 0.0020
-7.250 -0.3225 0.01195 0.00664 -0.1148 0.8439 0.0020
-7.000 -0.2983 0.01142 0.00596 -0.1144 0.8300 0.0021
-6.750 -0.2737 0.01094 0.00534 -0.1141 0.8177 0.0021
-6.500 -0.2485 0.01054 0.00481 -0.1138 0.8062 0.0022
-6.250 -0.2228 0.01018 0.00435 -0.1136 0.7950 0.0023
-6.000 -0.1965 0.00989 0.00394 -0.1135 0.7852 0.0024
-5.750 -0.1703 0.00954 0.00348 -0.1134 0.7764 0.0028
-5.500 -0.1437 0.00927 0.00315 -0.1133 0.7676 0.0037
-5.250 -0.1167 0.00907 0.00288 -0.1133 0.7593 0.0047
-5.000 -0.0898 0.00886 0.00263 -0.1133 0.7515 0.0078
-4.750 -0.0625 0.00863 0.00241 -0.1134 0.7443 0.0145
-4.500 -0.0353 0.00845 0.00222 -0.1135 0.7375 0.0232
-4.250 -0.0080 0.00819 0.00201 -0.1136 0.7306 0.0431
-4.000 0.0191 0.00792 0.00183 -0.1138 0.7242 0.0740
-3.750 0.0469 0.00771 0.00168 -0.1139 0.7182 0.0996
-3.500 0.0743 0.00748 0.00153 -0.1141 0.7124 0.1378
-3.250 0.1021 0.00723 0.00139 -0.1144 0.7070 0.1815
-3.000 0.1297 0.00694 0.00124 -0.1146 0.7011 0.2381
-2.750 0.1572 0.00660 0.00111 -0.1149 0.6962 0.3189
-2.500 0.1851 0.00633 0.00105 -0.1152 0.6913 0.3901
-2.250 0.2131 0.00627 0.00102 -0.1154 0.6861 0.4155
-2.000 0.2412 0.00625 0.00099 -0.1155 0.6815 0.4314
-1.750 0.2695 0.00621 0.00098 -0.1157 0.6768 0.4495
-1.500 0.2976 0.00620 0.00098 -0.1158 0.6722 0.4686
-1.250 0.3258 0.00620 0.00097 -0.1159 0.6680 0.4833
-1.000 0.3541 0.00619 0.00098 -0.1161 0.6635 0.4937
-0.750 0.3823 0.00620 0.00098 -0.1162 0.6591 0.5005
-0.500 0.4104 0.00622 0.00099 -0.1163 0.6552 0.5065
0.000 0.4669 0.00624 0.00102 -0.1166 0.6467 0.5170
0.250 0.4949 0.00628 0.00105 -0.1167 0.6427 0.5225
0.500 0.5232 0.00629 0.00107 -0.1168 0.6387 0.5275
0.750 0.5513 0.00631 0.00111 -0.1169 0.6342 0.5332
1.000 0.5790 0.00636 0.00115 -0.1170 0.6289 0.5387
1.250 0.6070 0.00638 0.00119 -0.1170 0.6218 0.5444
1.500 0.6343 0.00644 0.00124 -0.1170 0.6138 0.5506
1.750 0.6620 0.00648 0.00130 -0.1170 0.6047 0.5565
2.000 0.6893 0.00653 0.00136 -0.1170 0.5944 0.5632
2.250 0.7163 0.00661 0.00143 -0.1168 0.5822 0.5696
2.500 0.7428 0.00670 0.00151 -0.1166 0.5647 0.5769
2.750 0.7686 0.00685 0.00160 -0.1163 0.5424 0.5841
3.000 0.7947 0.00698 0.00171 -0.1160 0.5221 0.5921
3.250 0.8200 0.00717 0.00184 -0.1156 0.4948 0.5999
3.500 0.8436 0.00750 0.00202 -0.1149 0.4530 0.6089
3.750 0.8639 0.00807 0.00234 -0.1136 0.3841 0.6179
4.000 0.8847 0.00864 0.00267 -0.1125 0.3251 0.6269
4.250 0.9036 0.00935 0.00307 -0.1111 0.2517 0.6370
4.500 0.9227 0.01002 0.00347 -0.1097 0.1878 0.6483
4.750 0.9449 0.01044 0.00379 -0.1088 0.1526 0.6603
5.000 0.9672 0.01085 0.00413 -0.1080 0.1239 0.6728
5.250 0.9887 0.01129 0.00448 -0.1070 0.0947 0.6866
5.500 1.0100 0.01174 0.00485 -0.1060 0.0685 0.7024
5.750 1.0309 0.01222 0.00524 -0.1048 0.0448 0.7202
6.000 1.0524 0.01261 0.00562 -0.1039 0.0303 0.7394
6.250 1.0739 0.01299 0.00600 -0.1028 0.0202 0.7609
6.500 1.0956 0.01332 0.00639 -0.1019 0.0149 0.7872
6.750 1.1165 0.01365 0.00679 -0.1007 0.0105 0.8206
7.000 1.1357 0.01392 0.00722 -0.0992 0.0073 0.8688
7.250 1.1501 0.01416 0.00762 -0.0965 0.0041 1.0000
7.500 1.1699 0.01465 0.00812 -0.0952 0.0026 1.0000
7.750 1.1899 0.01510 0.00860 -0.0940 0.0021 1.0000
8.000 1.2084 0.01558 0.00912 -0.0925 0.0018 1.0000
8.250 1.2246 0.01613 0.00972 -0.0905 0.0016 1.0000
8.500 1.2396 0.01674 0.01040 -0.0883 0.0014 1.0000
8.750 1.2529 0.01747 0.01121 -0.0859 0.0013 1.0000
9.000 1.2677 0.01811 0.01191 -0.0839 0.0013 1.0000
9.250 1.2817 0.01881 0.01271 -0.0817 0.0013 1.0000
9.500 1.2953 0.01954 0.01351 -0.0796 0.0013 1.0000
9.750 1.3080 0.02034 0.01439 -0.0774 0.0013 1.0000
10.000 1.3198 0.02122 0.01535 -0.0752 0.0012 1.0000
10.250 1.3301 0.02222 0.01644 -0.0729 0.0012 1.0000
10.500 1.3410 0.02320 0.01751 -0.0707 0.0012 1.0000
10.750 1.3510 0.02427 0.01867 -0.0686 0.0012 1.0000
11.000 1.3613 0.02534 0.01982 -0.0666 0.0011 1.0000
11.250 1.3693 0.02663 0.02122 -0.0645 0.0011 1.0000
11.500 1.3779 0.02792 0.02261 -0.0626 0.0011 1.0000
11.750 1.3862 0.02926 0.02405 -0.0608 0.0011 1.0000
12.000 1.3943 0.03066 0.02554 -0.0591 0.0010 1.0000
12.250 1.4002 0.03231 0.02733 -0.0574 0.0010 1.0000
12.500 1.4049 0.03413 0.02928 -0.0557 0.0010 1.0000
12.750 1.4107 0.03588 0.03113 -0.0543 0.0010 1.0000
13.000 1.4153 0.03780 0.03317 -0.0530 0.0009 1.0000
13.250 1.4172 0.04007 0.03557 -0.0517 0.0009 1.0000
13.500 1.4185 0.04248 0.03811 -0.0506 0.0009 1.0000
13.750 1.4166 0.04533 0.04112 -0.0496 0.0009 1.0000
14.000 1.4153 0.04821 0.04413 -0.0488 0.0009 1.0000
14.250 1.4119 0.05145 0.04752 -0.0483 0.0009 1.0000
14.500 1.4077 0.05490 0.05113 -0.0480 0.0009 1.0000
14.750 1.4013 0.05881 0.05519 -0.0480 0.0009 1.0000
15.000 1.3938 0.06306 0.05961 -0.0484 0.0009 1.0000
15.250 1.3847 0.06775 0.06446 -0.0492 0.0009 1.0000
15.500 1.3744 0.07287 0.06974 -0.0505 0.0009 1.0000
15.750 1.3644 0.07823 0.07525 -0.0522 0.0008 1.0000
16.000 1.3479 0.08502 0.08222 -0.0547 0.0009 1.0000
16.250 1.3328 0.09200 0.08937 -0.0578 0.0008 1.0000
16.500 1.3157 0.09983 0.09736 -0.0617 0.0009 1.0000
16.750 1.2978 0.10834 0.10604 -0.0663 0.0009 1.0000
17.000 1.2757 0.11836 0.11624 -0.0721 0.0009 1.0000
17.250 1.2531 0.12921 0.12726 -0.0786 0.0009 1.0000
17.500 1.2279 0.14132 0.13953 -0.0860 0.0009 1.0000
17.750 1.2013 0.15435 0.15271 -0.0939 0.0009 1.0000
18.000 1.1724 0.16854 0.16705 -0.1023 0.0009 1.0000
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