EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.97 at α=-0.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ec863914-il-1000000-n5.txt Download as CSV file: xf-ec863914-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EC 86(-3)-914 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.0297 0.10299 0.10100 -0.1380 0.9570 0.0040
-14.500 -0.1390 0.10975 0.10762 -0.1366 0.9676 0.0036
-14.250 -0.1511 0.10068 0.09850 -0.1407 0.9666 0.0036
-14.000 -0.1500 0.09545 0.09323 -0.1439 0.9658 0.0036
-13.750 -0.1637 0.08658 0.08428 -0.1495 0.9649 0.0036
-13.500 -0.1769 0.07819 0.07578 -0.1558 0.9640 0.0036
-13.250 -0.1869 0.07073 0.06822 -0.1623 0.9630 0.0036
-13.000 -0.1922 0.06437 0.06175 -0.1684 0.9618 0.0036
-12.750 -0.2073 0.05833 0.05559 -0.1730 0.9593 0.0036
-12.500 -0.2070 0.05511 0.05233 -0.1749 0.9572 0.0036
-12.250 -0.2132 0.05079 0.04790 -0.1786 0.9547 0.0036
-12.000 -0.2289 0.04538 0.04230 -0.1836 0.9518 0.0036
-11.750 -0.2280 0.04238 0.03919 -0.1866 0.9498 0.0036
-11.500 -0.2442 0.03931 0.03597 -0.1868 0.9462 0.0036
-11.250 -0.2523 0.03706 0.03360 -0.1867 0.9427 0.0036
-11.000 -0.2569 0.03487 0.03128 -0.1867 0.9396 0.0036
-10.750 -0.2584 0.03290 0.02917 -0.1867 0.9367 0.0036
-10.500 -0.2672 0.03129 0.02745 -0.1842 0.9331 0.0036
-10.250 -0.2702 0.03003 0.02611 -0.1816 0.9297 0.0036
-10.000 -0.2727 0.02837 0.02427 -0.1805 0.9265 0.0036
-9.750 -0.2640 0.02672 0.02242 -0.1805 0.9244 0.0036
-9.500 -0.2457 0.02329 0.01900 -0.1791 0.9239 0.0033
-9.000 -0.2207 0.02100 0.01644 -0.1775 0.9196 0.0034
-8.000 -0.1460 0.01639 0.01154 -0.1752 0.9137 0.0043
-7.500 -0.0969 0.01486 0.00988 -0.1761 0.9116 0.0064
-7.250 -0.0705 0.01418 0.00914 -0.1765 0.9108 0.0063
-7.000 -0.0454 0.01369 0.00860 -0.1766 0.9098 0.0061
-6.750 -0.0212 0.01356 0.00842 -0.1761 0.9084 0.0058
-6.500 0.0029 0.01316 0.00800 -0.1759 0.9068 0.0058
-6.000 0.0566 0.01166 0.00647 -0.1774 0.9041 0.0060
-5.750 0.0865 0.01129 0.00607 -0.1783 0.9031 0.0059
-5.500 0.1181 0.01085 0.00562 -0.1796 0.9020 0.0055
-5.250 0.1513 0.01032 0.00503 -0.1812 0.9008 0.0052
-5.000 0.1847 0.00990 0.00457 -0.1828 0.8996 0.0050
-4.750 0.2165 0.00958 0.00423 -0.1839 0.8982 0.0049
-4.500 0.2426 0.00936 0.00400 -0.1838 0.8959 0.0048
-4.250 0.2717 0.00915 0.00377 -0.1843 0.8940 0.0046
-4.000 0.3022 0.00894 0.00354 -0.1851 0.8923 0.0045
-3.750 0.3338 0.00874 0.00332 -0.1860 0.8906 0.0044
-3.500 0.3668 0.00852 0.00308 -0.1872 0.8885 0.0044
-3.250 0.3967 0.00835 0.00289 -0.1878 0.8853 0.0043
-3.000 0.4236 0.00821 0.00274 -0.1877 0.8804 0.0044
-2.750 0.4570 0.00800 0.00249 -0.1889 0.8758 0.0044
-2.500 0.4811 0.00790 0.00239 -0.1881 0.8685 0.0045
-2.250 0.5133 0.00777 0.00223 -0.1891 0.8638 0.0047
-2.000 0.5389 0.00769 0.00216 -0.1887 0.8556 0.0052
-1.750 0.5789 0.00691 0.00188 -0.1922 0.8423 0.1941
-1.500 0.6154 0.00647 0.00174 -0.1947 0.8248 0.2963
-1.250 0.6439 0.00641 0.00165 -0.1950 0.7953 0.3283
-1.000 0.6645 0.00660 0.00167 -0.1936 0.7482 0.3588
-0.750 0.6841 0.00682 0.00179 -0.1920 0.7102 0.3943
-0.500 0.7052 0.00700 0.00191 -0.1908 0.6785 0.4318
-0.250 0.7260 0.00719 0.00205 -0.1896 0.6456 0.4688
0.000 0.7450 0.00740 0.00221 -0.1881 0.6071 0.5177
0.250 0.7644 0.00768 0.00246 -0.1866 0.5665 0.5770
0.500 0.7824 0.00807 0.00272 -0.1847 0.5277 0.6036
0.750 0.8027 0.00842 0.00295 -0.1833 0.4958 0.6175
1.000 0.8240 0.00876 0.00315 -0.1821 0.4667 0.6275
1.250 0.8458 0.00910 0.00337 -0.1810 0.4383 0.6349
1.500 0.8681 0.00942 0.00357 -0.1801 0.4119 0.6401
1.750 0.8906 0.00974 0.00379 -0.1791 0.3873 0.6447
2.000 0.9130 0.01008 0.00402 -0.1782 0.3628 0.6503
2.250 0.9357 0.01041 0.00424 -0.1773 0.3393 0.6565
2.500 0.9583 0.01074 0.00449 -0.1764 0.3184 0.6620
2.750 0.9818 0.01104 0.00471 -0.1757 0.3021 0.6666
3.000 1.0056 0.01132 0.00493 -0.1751 0.2875 0.6701
3.250 1.0290 0.01160 0.00517 -0.1743 0.2738 0.6738
3.500 1.0525 0.01188 0.00541 -0.1736 0.2614 0.6779
3.750 1.0760 0.01216 0.00565 -0.1729 0.2504 0.6814
4.000 1.0996 0.01244 0.00589 -0.1722 0.2401 0.6842
4.500 1.1463 0.01300 0.00642 -0.1708 0.2206 0.6887
4.750 1.1697 0.01329 0.00669 -0.1701 0.2123 0.6902
5.000 1.1932 0.01357 0.00695 -0.1695 0.2052 0.6913
5.250 1.2160 0.01389 0.00725 -0.1687 0.1963 0.6925
5.500 1.2380 0.01426 0.00757 -0.1678 0.1853 0.6935
5.750 1.2608 0.01458 0.00787 -0.1671 0.1769 0.6946
6.000 1.2832 0.01493 0.00820 -0.1662 0.1683 0.6955
6.250 1.3048 0.01534 0.00855 -0.1653 0.1577 0.6965
6.500 1.3269 0.01572 0.00891 -0.1645 0.1477 0.6974
6.750 1.3468 0.01626 0.00935 -0.1633 0.1306 0.6982
7.000 1.3530 0.01790 0.01051 -0.1601 0.0583 0.6992
7.250 1.3595 0.01967 0.01196 -0.1567 0.0052 0.7003
7.500 1.3798 0.02018 0.01250 -0.1557 0.0035 0.7014
7.750 1.4002 0.02069 0.01305 -0.1546 0.0030 0.7025
8.000 1.4197 0.02126 0.01368 -0.1534 0.0026 0.7035
8.250 1.4385 0.02190 0.01437 -0.1521 0.0022 0.7045
8.500 1.4569 0.02255 0.01508 -0.1508 0.0020 0.7056
8.750 1.4756 0.02317 0.01575 -0.1495 0.0019 0.7067
9.000 1.4934 0.02386 0.01649 -0.1481 0.0018 0.7078
9.250 1.5105 0.02459 0.01728 -0.1467 0.0016 0.7089
9.500 1.5275 0.02534 0.01808 -0.1452 0.0015 0.7100
9.750 1.5437 0.02614 0.01894 -0.1437 0.0014 0.7110
10.000 1.5596 0.02695 0.01980 -0.1422 0.0012 0.7121
10.250 1.5744 0.02786 0.02077 -0.1405 0.0011 0.7130
10.500 1.5872 0.02896 0.02195 -0.1387 0.0010 0.7141
10.750 1.5973 0.03030 0.02340 -0.1365 0.0009 0.7152
11.000 1.6076 0.03159 0.02479 -0.1344 0.0009 0.7163
11.250 1.6198 0.03274 0.02601 -0.1326 0.0009 0.7176
11.500 1.6305 0.03401 0.02737 -0.1307 0.0009 0.7189
11.750 1.6406 0.03535 0.02880 -0.1288 0.0008 0.7203
12.000 1.6505 0.03672 0.03024 -0.1270 0.0008 0.7216
12.250 1.6579 0.03833 0.03195 -0.1250 0.0008 0.7229
12.500 1.6637 0.04014 0.03387 -0.1229 0.0008 0.7241
12.750 1.6713 0.04181 0.03564 -0.1212 0.0007 0.7253
13.000 1.6770 0.04373 0.03765 -0.1194 0.0007 0.7265
13.250 1.6790 0.04605 0.04009 -0.1174 0.0007 0.7275
13.500 1.6840 0.04815 0.04228 -0.1159 0.0006 0.7287
13.750 1.6856 0.05071 0.04495 -0.1143 0.0006 0.7299
14.000 1.6877 0.05330 0.04766 -0.1129 0.0006 0.7311
14.250 1.6871 0.05630 0.05077 -0.1117 0.0005 0.7324
14.500 1.6846 0.05964 0.05425 -0.1106 0.0005 0.7336
14.750 1.6813 0.06326 0.05798 -0.1099 0.0005 0.7348
15.000 1.6821 0.06645 0.06127 -0.1095 0.0005 0.7362
15.250 1.6731 0.07118 0.06616 -0.1093 0.0005 0.7374
15.500 1.6685 0.07545 0.07055 -0.1095 0.0005 0.7386
15.750 1.6593 0.08063 0.07587 -0.1101 0.0005 0.7397
16.000 1.6524 0.08562 0.08098 -0.1111 0.0004 0.7409
16.250 1.6426 0.09131 0.08681 -0.1125 0.0004 0.7419
16.500 1.6272 0.09824 0.09390 -0.1147 0.0004 0.7428
17.000 1.5977 0.11250 0.10847 -0.1204 0.0004 0.7445
17.250 1.5830 0.11988 0.11600 -0.1237 0.0004 0.7455
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Polar data table (+)
Polar graphs
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