EPPLER 59 AIRFOIL (e59-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 59 AIRFOIL (e59-il) Reynolds number: 1,000,000 Max Cl/Cd: 188.81 at α=0.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e59-il-1000000.txt Download as CSV file: xf-e59-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 59 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2571 0.08649 0.08480 -0.0609 0.9799 0.0100
-7.500 -0.2467 0.08334 0.08166 -0.0634 0.9774 0.0105
-7.250 -0.2316 0.07919 0.07750 -0.0689 0.9748 0.0119
-7.000 -0.2067 0.07443 0.07274 -0.0766 0.9732 0.0121
-6.750 -0.1930 0.07054 0.06885 -0.0806 0.9691 0.0121
-6.500 -0.1749 0.06604 0.06435 -0.0863 0.9650 0.0122
-6.250 -0.1472 0.05762 0.05591 -0.0996 0.9625 0.0127
-6.000 -0.1195 0.05534 0.05361 -0.1041 0.9616 0.0134
-5.750 -0.0842 0.05121 0.04945 -0.1126 0.9607 0.0143
-5.500 -0.0314 0.04459 0.04273 -0.1267 0.9601 0.0169
-5.250 0.0760 0.01135 0.00702 -0.1675 0.9607 0.0131
-5.000 0.1101 0.01090 0.00652 -0.1690 0.9603 0.0142
-4.750 0.1446 0.01051 0.00607 -0.1705 0.9600 0.0155
-4.500 0.1789 0.01031 0.00582 -0.1720 0.9597 0.0168
-4.250 0.2003 0.00963 0.00503 -0.1707 0.9559 0.0188
-4.000 0.2282 0.00947 0.00487 -0.1707 0.9537 0.0206
-3.750 0.2595 0.00926 0.00464 -0.1715 0.9525 0.0227
-3.500 0.2928 0.00879 0.00411 -0.1728 0.9517 0.0258
-3.250 0.3256 0.00861 0.00394 -0.1738 0.9509 0.0291
-3.000 0.3591 0.00842 0.00373 -0.1751 0.9502 0.0317
-2.750 0.3938 0.00814 0.00343 -0.1766 0.9497 0.0338
-2.500 0.4297 0.00773 0.00300 -0.1784 0.9492 0.0386
-2.250 0.4663 0.00747 0.00273 -0.1803 0.9485 0.0418
-2.000 0.5030 0.00719 0.00244 -0.1821 0.9476 0.0442
-1.750 0.5393 0.00685 0.00211 -0.1839 0.9467 0.0526
-1.500 0.5627 0.00671 0.00199 -0.1828 0.9421 0.0635
-1.250 0.5932 0.00644 0.00183 -0.1834 0.9391 0.0961
-1.000 0.6267 0.00612 0.00171 -0.1847 0.9368 0.1719
-0.750 0.6636 0.00572 0.00144 -0.1866 0.9322 0.2250
-0.500 0.6913 0.00534 0.00132 -0.1865 0.9224 0.3420
-0.250 0.7214 0.00502 0.00126 -0.1870 0.9120 0.4571
0.000 0.7534 0.00474 0.00119 -0.1878 0.8962 0.5725
0.250 0.7842 0.00445 0.00118 -0.1884 0.8718 0.7099
0.500 0.8081 0.00428 0.00122 -0.1872 0.8374 0.8699
0.750 0.8231 0.00438 0.00120 -0.1838 0.7835 1.0000
1.000 0.8403 0.00493 0.00136 -0.1814 0.7050 1.0000
1.250 0.8523 0.00592 0.00169 -0.1779 0.5668 1.0000
1.500 0.8736 0.00647 0.00192 -0.1766 0.5082 1.0000
1.750 0.8971 0.00687 0.00210 -0.1758 0.4586 1.0000
2.000 0.9126 0.00810 0.00253 -0.1736 0.2892 1.0000
2.250 0.9350 0.00872 0.00281 -0.1726 0.2186 1.0000
2.500 0.9548 0.00971 0.00325 -0.1713 0.1011 1.0000
2.750 0.9776 0.01036 0.00361 -0.1703 0.0444 1.0000
3.000 1.0034 0.01062 0.00384 -0.1699 0.0378 1.0000
3.250 1.0291 0.01088 0.00411 -0.1694 0.0357 1.0000
3.500 1.0546 0.01116 0.00440 -0.1689 0.0344 1.0000
3.750 1.0800 0.01146 0.00473 -0.1684 0.0333 1.0000
4.000 1.1051 0.01179 0.00508 -0.1678 0.0321 1.0000
4.250 1.1298 0.01216 0.00548 -0.1671 0.0308 1.0000
4.500 1.1539 0.01263 0.00600 -0.1663 0.0293 1.0000
4.750 1.1766 0.01328 0.00674 -0.1653 0.0277 1.0000
5.000 1.2019 0.01351 0.00698 -0.1648 0.0271 1.0000
5.250 1.2269 0.01377 0.00725 -0.1643 0.0260 1.0000
5.500 1.2514 0.01410 0.00760 -0.1637 0.0245 1.0000
5.750 1.2755 0.01447 0.00800 -0.1630 0.0229 1.0000
6.000 1.2992 0.01488 0.00841 -0.1623 0.0211 1.0000
6.250 1.3189 0.01587 0.00948 -0.1608 0.0189 1.0000
6.500 1.3453 0.01585 0.00945 -0.1606 0.0179 1.0000
6.750 1.3705 0.01601 0.00961 -0.1602 0.0163 1.0000
7.000 1.3956 0.01615 0.00974 -0.1597 0.0149 1.0000
7.250 1.4158 0.01701 0.01063 -0.1583 0.0130 1.0000
7.500 1.4397 0.01730 0.01095 -0.1577 0.0122 1.0000
7.750 1.4635 0.01760 0.01125 -0.1570 0.0111 1.0000
8.000 1.4862 0.01801 0.01165 -0.1562 0.0101 1.0000
8.250 1.5023 0.01938 0.01316 -0.1540 0.0090 1.0000
8.500 1.5236 0.01995 0.01381 -0.1529 0.0086 1.0000
8.750 1.5438 0.02065 0.01459 -0.1516 0.0081 1.0000
9.000 1.5633 0.02143 0.01545 -0.1501 0.0076 1.0000
9.250 1.5826 0.02217 0.01627 -0.1487 0.0072 1.0000
9.500 1.6009 0.02301 0.01719 -0.1471 0.0069 1.0000
9.750 1.6160 0.02429 0.01857 -0.1450 0.0065 1.0000
10.000 1.6210 0.02745 0.02208 -0.1413 0.0060 1.0000
10.250 1.6369 0.02820 0.02295 -0.1393 0.0059 1.0000
10.500 1.6516 0.02888 0.02373 -0.1372 0.0056 1.0000
10.750 1.6628 0.03006 0.02504 -0.1345 0.0055 1.0000
11.000 1.6725 0.03137 0.02650 -0.1317 0.0052 1.0000
11.250 1.6801 0.03295 0.02824 -0.1286 0.0050 1.0000
11.500 1.6861 0.03461 0.03008 -0.1255 0.0049 1.0000
11.750 1.6915 0.03627 0.03190 -0.1224 0.0047 1.0000
12.000 1.6949 0.03813 0.03392 -0.1192 0.0046 1.0000
12.250 1.6978 0.03999 0.03592 -0.1162 0.0045 1.0000
12.500 1.6967 0.04234 0.03846 -0.1129 0.0044 1.0000
12.750 1.6944 0.04483 0.04112 -0.1097 0.0043 1.0000
13.000 1.6902 0.04754 0.04401 -0.1068 0.0042 1.0000
13.250 1.6773 0.05149 0.04819 -0.1036 0.0042 1.0000
13.500 1.6661 0.05530 0.05219 -0.1012 0.0041 1.0000
13.750 1.6512 0.05987 0.05698 -0.0993 0.0041 1.0000
14.000 1.6300 0.06565 0.06300 -0.0982 0.0041 1.0000
14.250 1.6121 0.07146 0.06901 -0.0983 0.0041 1.0000
14.500 1.5883 0.07882 0.07659 -0.0999 0.0040 1.0000
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Polar data table (+)
Polar graphs
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