EPPLER 678 AIRFOIL (e678-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 678 AIRFOIL (e678-il) Reynolds number: 1,000,000 Max Cl/Cd: 130.7 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e678-il-1000000-n5.txt Download as CSV file: xf-e678-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.2066 0.05222 0.04950 -0.1874 0.9132 0.0057
-13.000 -0.2429 0.04128 0.03829 -0.1959 0.9064 0.0057
-12.750 -0.2645 0.03530 0.03212 -0.2000 0.9004 0.0056
-12.500 -0.2761 0.03154 0.02817 -0.2019 0.8954 0.0056
-12.250 -0.2859 0.02863 0.02509 -0.2024 0.8916 0.0056
-12.000 -0.2922 0.02645 0.02277 -0.2016 0.8880 0.0056
-11.750 -0.2965 0.02458 0.02075 -0.2004 0.8845 0.0057
-11.500 -0.2839 0.02394 0.02004 -0.1997 0.8816 0.0058
-11.250 -0.2810 0.02273 0.01869 -0.1983 0.8782 0.0058
-10.750 -0.2839 0.02041 0.01614 -0.1930 0.8724 0.0058
-10.500 -0.2772 0.01917 0.01474 -0.1912 0.8691 0.0058
-10.250 -0.2678 0.01790 0.01330 -0.1897 0.8658 0.0060
-10.000 -0.2520 0.01699 0.01226 -0.1889 0.8630 0.0060
-9.750 -0.2349 0.01622 0.01140 -0.1880 0.8606 0.0061
-9.500 -0.2162 0.01554 0.01064 -0.1873 0.8580 0.0062
-9.250 -0.1956 0.01498 0.01001 -0.1867 0.8549 0.0063
-9.000 -0.1741 0.01444 0.00940 -0.1863 0.8517 0.0064
-8.750 -0.1513 0.01395 0.00883 -0.1860 0.8484 0.0065
-8.500 -0.1291 0.01344 0.00825 -0.1855 0.8451 0.0066
-8.250 -0.1069 0.01300 0.00775 -0.1850 0.8398 0.0067
-8.000 -0.0840 0.01258 0.00726 -0.1846 0.8336 0.0069
-7.750 -0.0612 0.01216 0.00679 -0.1841 0.8259 0.0071
-7.500 -0.0432 0.01185 0.00633 -0.1824 0.7918 0.0073
-7.250 -0.0463 0.01206 0.00615 -0.1761 0.7260 0.0074
-7.000 -0.0282 0.01185 0.00582 -0.1745 0.7139 0.0076
-6.750 -0.0061 0.01161 0.00550 -0.1737 0.7069 0.0078
-6.250 0.0400 0.01115 0.00492 -0.1725 0.6970 0.0081
-6.000 0.0642 0.01075 0.00445 -0.1722 0.6932 0.0085
-5.750 0.0881 0.01048 0.00414 -0.1718 0.6896 0.0089
-5.500 0.1119 0.01028 0.00389 -0.1712 0.6862 0.0091
-5.250 0.1360 0.01010 0.00367 -0.1708 0.6830 0.0095
-5.000 0.1621 0.00991 0.00346 -0.1707 0.6805 0.0100
-4.750 0.1881 0.00974 0.00326 -0.1706 0.6778 0.0104
-4.500 0.2140 0.00961 0.00309 -0.1705 0.6750 0.0108
-4.250 0.2402 0.00945 0.00291 -0.1704 0.6724 0.0119
-4.000 0.2662 0.00933 0.00277 -0.1703 0.6700 0.0132
-3.750 0.2925 0.00922 0.00264 -0.1702 0.6677 0.0158
-3.500 0.3202 0.00905 0.00251 -0.1705 0.6658 0.0274
-3.250 0.3483 0.00889 0.00241 -0.1709 0.6641 0.0432
-3.000 0.3763 0.00876 0.00233 -0.1713 0.6621 0.0590
-2.750 0.4046 0.00858 0.00226 -0.1717 0.6600 0.0885
-2.250 0.4616 0.00822 0.00216 -0.1729 0.6556 0.1796
-2.000 0.4901 0.00807 0.00214 -0.1734 0.6535 0.2320
-1.750 0.5198 0.00784 0.00213 -0.1744 0.6516 0.3118
-1.500 0.5495 0.00768 0.00213 -0.1752 0.6500 0.3757
-1.250 0.5807 0.00745 0.00215 -0.1765 0.6485 0.4682
-1.000 0.6102 0.00734 0.00218 -0.1772 0.6469 0.5194
-0.750 0.6389 0.00730 0.00222 -0.1776 0.6450 0.5558
-0.500 0.6673 0.00725 0.00227 -0.1780 0.6429 0.5969
-0.250 0.6950 0.00725 0.00235 -0.1782 0.6409 0.6310
0.000 0.7221 0.00729 0.00242 -0.1783 0.6391 0.6544
0.250 0.7489 0.00736 0.00249 -0.1782 0.6373 0.6718
0.500 0.7756 0.00744 0.00257 -0.1782 0.6353 0.6863
0.750 0.8024 0.00749 0.00265 -0.1781 0.6332 0.6957
1.000 0.8287 0.00754 0.00271 -0.1780 0.6299 0.7030
1.250 0.8539 0.00761 0.00278 -0.1776 0.6255 0.7088
1.500 0.8785 0.00771 0.00286 -0.1771 0.6216 0.7147
1.750 0.9034 0.00782 0.00295 -0.1768 0.6184 0.7202
2.000 0.9297 0.00787 0.00303 -0.1766 0.6154 0.7251
2.250 0.9552 0.00794 0.00312 -0.1763 0.6117 0.7299
2.500 0.9799 0.00804 0.00321 -0.1759 0.6077 0.7341
2.750 1.0040 0.00817 0.00332 -0.1754 0.6038 0.7375
3.000 1.0296 0.00824 0.00342 -0.1751 0.6002 0.7406
3.250 1.0549 0.00832 0.00352 -0.1749 0.5959 0.7437
3.500 1.0790 0.00843 0.00365 -0.1743 0.5911 0.7470
3.750 1.1025 0.00857 0.00377 -0.1737 0.5861 0.7500
4.000 1.1270 0.00868 0.00389 -0.1733 0.5802 0.7530
4.250 1.1486 0.00885 0.00406 -0.1722 0.5728 0.7556
4.500 1.1724 0.00897 0.00420 -0.1717 0.5654 0.7585
4.750 1.1935 0.00917 0.00439 -0.1706 0.5564 0.7616
5.000 1.2163 0.00933 0.00456 -0.1699 0.5459 0.7654
5.250 1.2358 0.00960 0.00479 -0.1685 0.5307 0.7694
5.500 1.2524 0.00996 0.00509 -0.1666 0.5107 0.7727
6.000 1.2734 0.01131 0.00608 -0.1607 0.4350 0.7784
6.250 1.2849 0.01202 0.00663 -0.1581 0.4010 0.7815
6.500 1.2977 0.01270 0.00717 -0.1557 0.3705 0.7843
6.750 1.3088 0.01346 0.00777 -0.1531 0.3385 0.7868
7.000 1.3197 0.01424 0.00841 -0.1505 0.3072 0.7893
7.250 1.3272 0.01520 0.00919 -0.1474 0.2699 0.7922
7.500 1.3332 0.01626 0.01006 -0.1442 0.2327 0.7954
7.750 1.3414 0.01723 0.01089 -0.1414 0.2036 0.7986
8.000 1.3529 0.01807 0.01163 -0.1392 0.1819 0.8015
8.250 1.3639 0.01894 0.01243 -0.1369 0.1628 0.8042
8.500 1.3741 0.01987 0.01328 -0.1346 0.1440 0.8072
8.750 1.3833 0.02089 0.01422 -0.1322 0.1231 0.8104
9.000 1.3916 0.02199 0.01524 -0.1297 0.1047 0.8140
9.250 1.4016 0.02304 0.01622 -0.1276 0.0883 0.8176
9.500 1.4093 0.02425 0.01737 -0.1252 0.0720 0.8211
9.750 1.4168 0.02551 0.01857 -0.1228 0.0561 0.8249
10.000 1.4229 0.02691 0.01991 -0.1204 0.0415 0.8289
10.250 1.4322 0.02816 0.02112 -0.1185 0.0321 0.8328
10.500 1.4390 0.02959 0.02253 -0.1163 0.0221 0.8368
10.750 1.4447 0.03118 0.02410 -0.1141 0.0121 0.8415
11.000 1.4551 0.03244 0.02539 -0.1126 0.0100 0.8466
11.250 1.4659 0.03371 0.02671 -0.1111 0.0088 0.8520
11.500 1.4772 0.03494 0.02801 -0.1098 0.0082 0.8587
12.000 1.4989 0.03757 0.03078 -0.1072 0.0074 0.8744
12.250 1.5083 0.03904 0.03232 -0.1059 0.0070 0.8845
12.500 1.5168 0.04057 0.03394 -0.1045 0.0067 0.8995
12.750 1.5227 0.04196 0.03549 -0.1026 0.0065 0.9598
13.000 1.5326 0.04351 0.03710 -0.1016 0.0063 1.0000
13.250 1.5421 0.04521 0.03886 -0.1007 0.0062 1.0000
13.500 1.5516 0.04693 0.04064 -0.0999 0.0060 1.0000
13.750 1.5603 0.04876 0.04253 -0.0991 0.0059 1.0000
14.000 1.5685 0.05067 0.04450 -0.0983 0.0057 1.0000
14.250 1.5764 0.05264 0.04653 -0.0975 0.0056 1.0000
14.500 1.5836 0.05471 0.04867 -0.0968 0.0055 1.0000
14.750 1.5902 0.05686 0.05088 -0.0961 0.0053 1.0000
15.000 1.5959 0.05913 0.05322 -0.0955 0.0052 1.0000
15.250 1.6007 0.06155 0.05571 -0.0949 0.0051 1.0000
15.500 1.6050 0.06407 0.05831 -0.0943 0.0050 1.0000
15.750 1.6077 0.06682 0.06113 -0.0938 0.0049 1.0000
16.000 1.6087 0.06984 0.06424 -0.0933 0.0048 1.0000
16.250 1.6086 0.07304 0.06753 -0.0929 0.0047 1.0000
16.500 1.6113 0.07593 0.07051 -0.0927 0.0047 1.0000
16.750 1.6145 0.07880 0.07346 -0.0926 0.0046 1.0000
17.000 1.6170 0.08181 0.07655 -0.0926 0.0046 1.0000
17.250 1.6187 0.08498 0.07981 -0.0927 0.0045 1.0000
17.500 1.6202 0.08820 0.08313 -0.0929 0.0044 1.0000
17.750 1.6206 0.09164 0.08666 -0.0932 0.0044 1.0000
18.000 1.6205 0.09517 0.09028 -0.0936 0.0043 1.0000
18.250 1.6197 0.09887 0.09407 -0.0942 0.0042 1.0000
18.500 1.6177 0.10280 0.09810 -0.0949 0.0042 1.0000
18.750 1.6152 0.10687 0.10227 -0.0958 0.0041 1.0000
19.000 1.6124 0.11101 0.10651 -0.0968 0.0041 1.0000
19.250 1.6091 0.11527 0.11087 -0.0980 0.0040 1.0000
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