EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 68 AIRFOIL (e68-il) Reynolds number: 500,000 Max Cl/Cd: 102.6 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e68-il-500000-n5.txt Download as CSV file: xf-e68-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 68 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6325 0.08450 0.08171 -0.0639 1.0000 0.0081
-13.750 -0.6752 0.07338 0.07043 -0.0696 1.0000 0.0080
-13.500 -0.7125 0.06392 0.06079 -0.0744 1.0000 0.0079
-13.250 -0.7391 0.05693 0.05367 -0.0778 1.0000 0.0078
-13.000 -0.7573 0.05053 0.04711 -0.0822 0.9994 0.0078
-12.750 -0.7571 0.04439 0.04080 -0.0899 0.9966 0.0079
-12.500 -0.7516 0.03962 0.03583 -0.0965 0.9932 0.0080
-12.250 -0.7464 0.03557 0.03158 -0.1016 0.9883 0.0080
-12.000 -0.7350 0.03235 0.02818 -0.1063 0.9843 0.0082
-11.750 -0.7271 0.03019 0.02587 -0.1078 0.9771 0.0082
-11.500 -0.7131 0.02810 0.02361 -0.1096 0.9722 0.0084
-11.250 -0.7006 0.02651 0.02186 -0.1095 0.9651 0.0085
-11.000 -0.6805 0.02496 0.02015 -0.1106 0.9610 0.0087
-10.750 -0.6560 0.02349 0.01852 -0.1121 0.9586 0.0088
-10.500 -0.6384 0.02239 0.01729 -0.1117 0.9519 0.0091
-10.250 -0.6138 0.02124 0.01599 -0.1126 0.9481 0.0093
-10.000 -0.5864 0.02012 0.01472 -0.1139 0.9453 0.0095
-9.750 -0.5645 0.01922 0.01371 -0.1137 0.9395 0.0097
-9.500 -0.5388 0.01835 0.01272 -0.1143 0.9350 0.0099
-9.250 -0.5104 0.01751 0.01176 -0.1153 0.9315 0.0101
-9.000 -0.4862 0.01683 0.01097 -0.1153 0.9261 0.0103
-8.750 -0.4621 0.01596 0.01000 -0.1154 0.9205 0.0106
-8.500 -0.4350 0.01516 0.00911 -0.1160 0.9163 0.0110
-8.250 -0.4119 0.01461 0.00849 -0.1155 0.9100 0.0115
-8.000 -0.3856 0.01412 0.00792 -0.1156 0.9047 0.0120
-7.750 -0.3587 0.01366 0.00738 -0.1158 0.9000 0.0127
-7.500 -0.3343 0.01325 0.00689 -0.1155 0.8938 0.0133
-7.250 -0.3076 0.01285 0.00639 -0.1155 0.8887 0.0138
-7.000 -0.2825 0.01239 0.00587 -0.1153 0.8832 0.0148
-6.750 -0.2570 0.01202 0.00546 -0.1150 0.8773 0.0161
-6.500 -0.2298 0.01170 0.00505 -0.1151 0.8724 0.0179
-6.250 -0.2048 0.01135 0.00470 -0.1147 0.8664 0.0218
-6.000 -0.1788 0.01102 0.00436 -0.1146 0.8607 0.0304
-5.750 -0.1524 0.01069 0.00406 -0.1145 0.8555 0.0424
-5.500 -0.1267 0.01040 0.00380 -0.1143 0.8493 0.0543
-5.250 -0.0998 0.01016 0.00356 -0.1142 0.8438 0.0665
-5.000 -0.0735 0.00993 0.00335 -0.1141 0.8380 0.0796
-4.750 -0.0470 0.00969 0.00315 -0.1140 0.8319 0.0973
-4.500 -0.0202 0.00944 0.00295 -0.1140 0.8264 0.1194
-4.250 0.0059 0.00920 0.00278 -0.1138 0.8201 0.1447
-4.000 0.0329 0.00900 0.00262 -0.1138 0.8143 0.1696
-3.750 0.0595 0.00880 0.00248 -0.1137 0.8081 0.1939
-3.500 0.0865 0.00865 0.00235 -0.1136 0.8017 0.2165
-3.250 0.1135 0.00849 0.00224 -0.1136 0.7958 0.2424
-3.000 0.1402 0.00831 0.00214 -0.1134 0.7889 0.2748
-2.750 0.1673 0.00816 0.00204 -0.1134 0.7828 0.3057
-2.000 0.2481 0.00780 0.00185 -0.1131 0.7620 0.3951
-1.750 0.2752 0.00772 0.00180 -0.1130 0.7552 0.4243
-1.500 0.3022 0.00763 0.00178 -0.1129 0.7478 0.4522
-1.250 0.3292 0.00758 0.00175 -0.1128 0.7406 0.4784
-1.000 0.3562 0.00753 0.00175 -0.1126 0.7332 0.5040
-0.750 0.3831 0.00749 0.00174 -0.1125 0.7257 0.5290
-0.500 0.4101 0.00745 0.00175 -0.1123 0.7180 0.5524
0.000 0.4637 0.00742 0.00179 -0.1119 0.7020 0.5976
0.250 0.4902 0.00742 0.00182 -0.1116 0.6940 0.6201
0.500 0.5168 0.00742 0.00186 -0.1114 0.6852 0.6419
0.750 0.5431 0.00743 0.00190 -0.1111 0.6765 0.6638
1.000 0.5691 0.00747 0.00196 -0.1107 0.6669 0.6856
1.250 0.5951 0.00749 0.00202 -0.1103 0.6568 0.7066
1.500 0.6207 0.00753 0.00209 -0.1098 0.6467 0.7273
2.000 0.6715 0.00765 0.00226 -0.1087 0.6253 0.7653
2.250 0.6964 0.00772 0.00235 -0.1081 0.6139 0.7831
2.500 0.7208 0.00780 0.00245 -0.1073 0.6018 0.8002
2.750 0.7448 0.00790 0.00256 -0.1065 0.5891 0.8172
3.000 0.7683 0.00801 0.00267 -0.1056 0.5762 0.8340
3.250 0.7916 0.00812 0.00279 -0.1046 0.5633 0.8508
3.500 0.8141 0.00824 0.00292 -0.1035 0.5491 0.8672
3.750 0.8359 0.00837 0.00305 -0.1022 0.5342 0.8844
4.250 0.8761 0.00866 0.00332 -0.0989 0.5017 0.9230
4.500 0.8978 0.00881 0.00347 -0.0976 0.4841 0.9480
4.750 0.9285 0.00905 0.00364 -0.0985 0.4620 0.9883
5.000 0.9503 0.00933 0.00384 -0.0974 0.4403 1.0000
5.250 0.9710 0.00964 0.00406 -0.0962 0.4174 1.0000
5.500 0.9912 0.00997 0.00431 -0.0949 0.3942 1.0000
5.750 1.0103 0.01035 0.00458 -0.0934 0.3700 1.0000
6.000 1.0277 0.01074 0.00486 -0.0916 0.3431 1.0000
6.250 1.0436 0.01121 0.00519 -0.0896 0.3139 1.0000
6.500 1.0587 0.01172 0.00557 -0.0874 0.2841 1.0000
6.750 1.0742 0.01224 0.00597 -0.0854 0.2560 1.0000
7.000 1.0890 0.01281 0.00640 -0.0832 0.2275 1.0000
7.250 1.1038 0.01340 0.00685 -0.0812 0.2004 1.0000
7.500 1.1189 0.01397 0.00732 -0.0792 0.1781 1.0000
7.750 1.1322 0.01465 0.00786 -0.0770 0.1516 1.0000
8.000 1.1457 0.01532 0.00842 -0.0749 0.1284 1.0000
8.250 1.1590 0.01602 0.00901 -0.0728 0.1075 1.0000
8.500 1.1719 0.01674 0.00963 -0.0707 0.0893 1.0000
8.750 1.1863 0.01739 0.01024 -0.0688 0.0770 1.0000
9.000 1.2003 0.01807 0.01088 -0.0670 0.0659 1.0000
9.250 1.2144 0.01875 0.01155 -0.0652 0.0569 1.0000
9.500 1.2277 0.01950 0.01227 -0.0634 0.0485 1.0000
9.750 1.2403 0.02031 0.01306 -0.0615 0.0403 1.0000
10.250 1.2635 0.02209 0.01481 -0.0578 0.0261 1.0000
10.500 1.2748 0.02304 0.01575 -0.0559 0.0208 1.0000
10.750 1.2852 0.02407 0.01680 -0.0541 0.0166 1.0000
11.000 1.2958 0.02512 0.01788 -0.0524 0.0144 1.0000
11.250 1.3071 0.02614 0.01895 -0.0508 0.0131 1.0000
11.500 1.3170 0.02729 0.02014 -0.0492 0.0119 1.0000
11.750 1.3261 0.02853 0.02144 -0.0475 0.0112 1.0000
12.000 1.3358 0.02976 0.02275 -0.0461 0.0106 1.0000
12.250 1.3453 0.03103 0.02409 -0.0447 0.0101 1.0000
12.500 1.3541 0.03239 0.02553 -0.0433 0.0097 1.0000
12.750 1.3618 0.03387 0.02710 -0.0420 0.0093 1.0000
13.000 1.3682 0.03551 0.02881 -0.0407 0.0088 1.0000
13.250 1.3731 0.03734 0.03072 -0.0394 0.0084 1.0000
13.500 1.3757 0.03945 0.03292 -0.0382 0.0081 1.0000
13.750 1.3811 0.04136 0.03492 -0.0372 0.0079 1.0000
14.000 1.3854 0.04344 0.03710 -0.0364 0.0078 1.0000
14.250 1.3896 0.04558 0.03935 -0.0356 0.0076 1.0000
14.500 1.3922 0.04798 0.04185 -0.0350 0.0074 1.0000
14.750 1.3943 0.05052 0.04449 -0.0345 0.0072 1.0000
15.000 1.3963 0.05314 0.04722 -0.0342 0.0071 1.0000
15.250 1.3961 0.05611 0.05031 -0.0340 0.0070 1.0000
15.500 1.3969 0.05907 0.05337 -0.0341 0.0068 1.0000
15.750 1.3957 0.06238 0.05679 -0.0343 0.0066 1.0000
16.000 1.3958 0.06559 0.06010 -0.0346 0.0064 1.0000
16.250 1.3936 0.06922 0.06383 -0.0352 0.0063 1.0000
16.500 1.3898 0.07320 0.06792 -0.0360 0.0062 1.0000
16.750 1.3833 0.07772 0.07257 -0.0371 0.0061 1.0000
17.000 1.3769 0.08233 0.07728 -0.0385 0.0059 1.0000
17.250 1.3692 0.08729 0.08237 -0.0401 0.0059 1.0000
17.500 1.3578 0.09297 0.08817 -0.0421 0.0057 1.0000
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Polar data table (+)
Polar graphs
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