EPPLER 678 AIRFOIL (e678-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 678 AIRFOIL (e678-il) Reynolds number: 1,000,000 Max Cl/Cd: 141.14 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e678-il-1000000.txt Download as CSV file: xf-e678-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 678 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
------ -------- --------- --------- -------- -------- --------
-13.250 0.0109 0.10804 0.10599 -0.1567 0.9621 0.0123
-13.000 0.0169 0.10447 0.10241 -0.1584 0.9595 0.0123
-12.750 0.0195 0.10167 0.09962 -0.1588 0.9559 0.0127
-12.500 0.0297 0.09850 0.09644 -0.1613 0.9540 0.0128
-12.250 0.0422 0.09542 0.09335 -0.1641 0.9525 0.0130
-12.000 0.0558 0.09240 0.09033 -0.1672 0.9511 0.0134
-11.750 0.0680 0.08858 0.08650 -0.1710 0.9496 0.0137
-11.500 0.1202 0.06480 0.06274 -0.1736 0.9303 0.0159
-11.250 0.1250 0.06188 0.05982 -0.1747 0.9277 0.0161
-11.000 0.1284 0.05837 0.05629 -0.1762 0.9253 0.0162
-10.750 0.1338 0.05517 0.05307 -0.1779 0.9230 0.0165
-10.500 0.1325 0.05106 0.04896 -0.1795 0.9202 0.0167
-10.250 -0.0252 0.03855 0.03601 -0.2079 0.9185 0.0160
-10.000 -0.0476 0.03556 0.03284 -0.2072 0.9123 0.0159
-9.750 -0.0642 0.03294 0.03006 -0.2058 0.9071 0.0160
-9.500 -0.0670 0.03197 0.02910 -0.2032 0.9036 0.0162
-9.250 -0.1522 0.01939 0.01519 -0.1941 0.8954 0.0100
-9.000 -0.1328 0.01820 0.01383 -0.1939 0.8929 0.0102
-8.750 -0.1180 0.01708 0.01257 -0.1925 0.8905 0.0103
-8.500 -0.0985 0.01644 0.01187 -0.1917 0.8878 0.0106
-8.250 -0.0777 0.01561 0.01091 -0.1911 0.8845 0.0108
-8.000 -0.0548 0.01484 0.01003 -0.1908 0.8817 0.0111
-7.750 -0.0296 0.01401 0.00907 -0.1910 0.8789 0.0113
-7.500 -0.0070 0.01346 0.00844 -0.1904 0.8760 0.0116
-7.250 0.0142 0.01287 0.00779 -0.1896 0.8725 0.0117
-7.000 0.0378 0.01234 0.00718 -0.1892 0.8689 0.0120
-6.750 0.0641 0.01188 0.00665 -0.1893 0.8653 0.0121
-6.500 0.0899 0.01148 0.00618 -0.1892 0.8615 0.0123
-6.250 0.1097 0.01071 0.00537 -0.1882 0.8563 0.0126
-6.000 0.1345 0.01017 0.00477 -0.1881 0.8505 0.0132
-5.750 0.1588 0.00985 0.00442 -0.1877 0.8442 0.0138
-5.500 0.1828 0.00953 0.00406 -0.1872 0.8351 0.0145
-5.250 0.2053 0.00925 0.00372 -0.1863 0.8215 0.0152
-4.500 0.2461 0.00906 0.00293 -0.1777 0.7248 0.0181
-4.250 0.2691 0.00897 0.00276 -0.1769 0.7177 0.0204
-4.000 0.2956 0.00874 0.00258 -0.1770 0.7132 0.0316
-3.750 0.3224 0.00851 0.00245 -0.1772 0.7088 0.0616
-3.500 0.3492 0.00836 0.00237 -0.1774 0.7046 0.0939
-3.250 0.3778 0.00818 0.00230 -0.1780 0.7010 0.1373
-3.000 0.4063 0.00793 0.00222 -0.1787 0.6982 0.1927
-2.750 0.4363 0.00762 0.00217 -0.1797 0.6954 0.2774
-2.500 0.4673 0.00730 0.00214 -0.1811 0.6927 0.3825
-2.250 0.4987 0.00705 0.00215 -0.1824 0.6900 0.4837
-2.000 0.5301 0.00698 0.00218 -0.1836 0.6872 0.5437
-1.750 0.5603 0.00692 0.00222 -0.1844 0.6848 0.5875
-1.500 0.5880 0.00688 0.00228 -0.1845 0.6828 0.6323
-1.250 0.6154 0.00690 0.00235 -0.1846 0.6805 0.6626
-1.000 0.6429 0.00695 0.00241 -0.1847 0.6783 0.6787
-0.750 0.6708 0.00702 0.00246 -0.1849 0.6762 0.6918
-0.500 0.6991 0.00711 0.00253 -0.1851 0.6740 0.7032
-0.250 0.7289 0.00722 0.00262 -0.1857 0.6717 0.7118
0.000 0.7599 0.00735 0.00271 -0.1866 0.6692 0.7205
0.250 0.7853 0.00738 0.00278 -0.1862 0.6676 0.7281
0.500 0.8112 0.00745 0.00285 -0.1860 0.6656 0.7354
0.750 0.8362 0.00750 0.00290 -0.1855 0.6628 0.7411
1.000 0.8601 0.00756 0.00297 -0.1848 0.6595 0.7459
1.250 0.8867 0.00767 0.00304 -0.1847 0.6559 0.7508
1.500 0.9155 0.00779 0.00313 -0.1851 0.6527 0.7551
1.750 0.9382 0.00781 0.00320 -0.1842 0.6503 0.7594
2.000 0.9621 0.00787 0.00328 -0.1836 0.6474 0.7637
2.250 0.9865 0.00794 0.00336 -0.1830 0.6443 0.7680
2.500 1.0118 0.00804 0.00344 -0.1827 0.6411 0.7714
2.750 1.0404 0.00814 0.00354 -0.1831 0.6375 0.7746
3.000 1.0625 0.00819 0.00364 -0.1821 0.6350 0.7777
3.250 1.0856 0.00826 0.00373 -0.1813 0.6317 0.7811
3.500 1.1094 0.00834 0.00382 -0.1807 0.6283 0.7843
3.750 1.1337 0.00845 0.00392 -0.1802 0.6244 0.7871
4.000 1.1577 0.00853 0.00403 -0.1796 0.6203 0.7900
4.250 1.1796 0.00860 0.00415 -0.1786 0.6163 0.7930
4.500 1.2020 0.00869 0.00428 -0.1777 0.6119 0.7961
4.750 1.2249 0.00883 0.00440 -0.1769 0.6073 0.7993
5.000 1.2480 0.00893 0.00454 -0.1762 0.6027 0.8024
5.250 1.2701 0.00902 0.00468 -0.1753 0.5972 0.8059
5.500 1.2904 0.00919 0.00485 -0.1740 0.5912 0.8094
5.750 1.3126 0.00930 0.00502 -0.1731 0.5848 0.8128
6.000 1.3324 0.00949 0.00520 -0.1718 0.5769 0.8160
6.250 1.3529 0.00965 0.00540 -0.1706 0.5662 0.8189
6.500 1.3699 0.00990 0.00564 -0.1687 0.5517 0.8220
6.750 1.3818 0.01032 0.00599 -0.1659 0.5269 0.8253
7.000 1.3883 0.01102 0.00651 -0.1622 0.4870 0.8292
7.250 1.3919 0.01197 0.00722 -0.1581 0.4411 0.8328
7.500 1.3977 0.01289 0.00795 -0.1545 0.4003 0.8364
7.750 1.4066 0.01372 0.00863 -0.1515 0.3675 0.8400
8.000 1.4153 0.01458 0.00936 -0.1486 0.3363 0.8441
8.250 1.4243 0.01548 0.01012 -0.1459 0.3067 0.8483
8.500 1.4320 0.01641 0.01094 -0.1429 0.2776 0.8527
8.750 1.4399 0.01738 0.01179 -0.1401 0.2508 0.8573
9.000 1.4464 0.01847 0.01275 -0.1371 0.2234 0.8623
9.250 1.4522 0.01960 0.01377 -0.1342 0.1965 0.8674
9.500 1.4581 0.02077 0.01483 -0.1313 0.1714 0.8734
9.750 1.4649 0.02194 0.01592 -0.1286 0.1499 0.8801
10.000 1.4706 0.02316 0.01708 -0.1259 0.1298 0.8884
10.250 1.4757 0.02447 0.01831 -0.1231 0.1096 0.8985
10.500 1.4801 0.02577 0.01958 -0.1203 0.0926 0.9142
10.750 1.4808 0.02710 0.02091 -0.1169 0.0751 1.0000
11.000 1.4853 0.02877 0.02249 -0.1146 0.0574 1.0000
11.250 1.4868 0.03072 0.02432 -0.1121 0.0395 1.0000
11.500 1.4862 0.03293 0.02642 -0.1095 0.0227 1.0000
11.750 1.4903 0.03485 0.02830 -0.1075 0.0146 1.0000
12.000 1.4982 0.03650 0.02997 -0.1060 0.0125 1.0000
12.250 1.5067 0.03814 0.03165 -0.1047 0.0113 1.0000
12.500 1.5165 0.03970 0.03328 -0.1035 0.0107 1.0000
12.750 1.5254 0.04139 0.03501 -0.1024 0.0102 1.0000
13.000 1.5332 0.04323 0.03691 -0.1013 0.0097 1.0000
13.250 1.5397 0.04524 0.03899 -0.1001 0.0093 1.0000
13.500 1.5435 0.04756 0.04139 -0.0989 0.0089 1.0000
13.750 1.5519 0.04943 0.04333 -0.0981 0.0087 1.0000
14.000 1.5591 0.05147 0.04544 -0.0972 0.0085 1.0000
14.250 1.5654 0.05364 0.04768 -0.0964 0.0083 1.0000
14.500 1.5712 0.05588 0.05000 -0.0956 0.0081 1.0000
14.750 1.5758 0.05829 0.05249 -0.0949 0.0079 1.0000
15.000 1.5798 0.06080 0.05508 -0.0942 0.0078 1.0000
15.250 1.5833 0.06342 0.05778 -0.0936 0.0076 1.0000
15.500 1.5858 0.06621 0.06065 -0.0931 0.0075 1.0000
15.750 1.5872 0.06918 0.06370 -0.0926 0.0073 1.0000
16.000 1.5862 0.07251 0.06711 -0.0922 0.0071 1.0000
16.250 1.5820 0.07632 0.07102 -0.0919 0.0069 1.0000
16.500 1.5740 0.08077 0.07559 -0.0917 0.0068 1.0000
16.750 1.5677 0.08510 0.08003 -0.0917 0.0067 1.0000
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