E62 (5.62%) (e62-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E62 (5.62%) (e62-il) Reynolds number: 500,000 Max Cl/Cd: 141.69 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e62-il-500000-n5.txt Download as CSV file: xf-e62-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E62 (5.62%)
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3044 0.11164 0.10928 -0.0384 0.9936 0.0076
-9.000 -0.2926 0.10830 0.10594 -0.0410 0.9919 0.0078
-8.750 -0.2799 0.10494 0.10258 -0.0438 0.9902 0.0082
-8.500 -0.2669 0.10157 0.09922 -0.0468 0.9886 0.0082
-8.250 -0.2528 0.09825 0.09589 -0.0500 0.9871 0.0083
-8.000 -0.2368 0.09483 0.09247 -0.0539 0.9857 0.0087
-7.750 -0.2232 0.09174 0.08939 -0.0571 0.9836 0.0088
-5.250 0.0015 0.03553 0.03327 -0.0981 0.9276 0.0093
-5.000 0.0315 0.03068 0.02838 -0.1059 0.9244 0.0094
-4.750 0.0674 0.02585 0.02347 -0.1146 0.9225 0.0094
-4.500 0.0973 0.01955 0.01707 -0.1243 0.9160 0.0105
-4.250 0.1318 0.01692 0.01436 -0.1299 0.9130 0.0120
-4.000 0.1774 0.01297 0.01022 -0.1387 0.9114 0.0132
-3.750 0.2257 0.00903 0.00598 -0.1472 0.9103 0.0132
-3.250 0.2919 0.01785 0.01387 -0.1582 0.9138 0.0090
-3.000 0.3370 0.01436 0.00982 -0.1628 0.9120 0.0084
-2.750 0.3791 0.01231 0.00734 -0.1661 0.9101 0.0081
-2.500 0.4160 0.01098 0.00571 -0.1681 0.9060 0.0081
-2.250 0.4519 0.01001 0.00453 -0.1698 0.9010 0.0083
-2.000 0.4898 0.00926 0.00363 -0.1720 0.8967 0.0088
-1.750 0.5235 0.00883 0.00310 -0.1732 0.8897 0.0093
-1.500 0.5601 0.00813 0.00230 -0.1752 0.8832 0.0117
-1.250 0.5926 0.00786 0.00194 -0.1762 0.8741 0.0122
-1.000 0.6249 0.00768 0.00165 -0.1771 0.8645 0.0128
-0.750 0.6560 0.00757 0.00144 -0.1777 0.8528 0.0142
-0.500 0.6857 0.00751 0.00130 -0.1780 0.8396 0.0200
-0.250 0.7156 0.00719 0.00128 -0.1787 0.8266 0.1535
0.000 0.7441 0.00702 0.00132 -0.1790 0.8131 0.2640
0.250 0.7732 0.00651 0.00151 -0.1798 0.7991 0.5675
0.500 0.7931 0.00598 0.00165 -0.1779 0.7856 0.8686
0.750 0.8165 0.00594 0.00161 -0.1767 0.7718 1.0000
1.000 0.8430 0.00608 0.00165 -0.1763 0.7569 1.0000
1.250 0.8691 0.00622 0.00170 -0.1759 0.7413 1.0000
1.500 0.8952 0.00636 0.00176 -0.1755 0.7262 1.0000
1.750 0.9211 0.00651 0.00184 -0.1750 0.7100 1.0000
2.000 0.9465 0.00668 0.00194 -0.1745 0.6918 1.0000
2.250 0.9714 0.00687 0.00205 -0.1738 0.6715 1.0000
2.500 0.9960 0.00708 0.00217 -0.1731 0.6478 1.0000
2.750 1.0201 0.00732 0.00231 -0.1723 0.6212 1.0000
3.000 1.0415 0.00773 0.00252 -0.1709 0.5748 1.0000
3.250 1.0556 0.00869 0.00289 -0.1683 0.4627 1.0000
3.500 1.0725 0.00966 0.00334 -0.1663 0.3652 1.0000
3.750 1.0912 0.01056 0.00379 -0.1648 0.2797 1.0000
4.000 1.1070 0.01182 0.00441 -0.1630 0.1634 1.0000
4.250 1.1259 0.01278 0.00496 -0.1615 0.0905 1.0000
4.500 1.1451 0.01372 0.00559 -0.1601 0.0322 1.0000
4.750 1.1669 0.01438 0.00614 -0.1590 0.0096 1.0000
5.000 1.1907 0.01477 0.00658 -0.1583 0.0084 1.0000
5.250 1.2141 0.01520 0.00706 -0.1575 0.0077 1.0000
5.500 1.2372 0.01566 0.00762 -0.1566 0.0073 1.0000
5.750 1.2597 0.01618 0.00822 -0.1556 0.0070 1.0000
6.000 1.2814 0.01679 0.00892 -0.1545 0.0064 1.0000
6.250 1.3014 0.01761 0.00984 -0.1531 0.0057 1.0000
6.500 1.3199 0.01858 0.01094 -0.1514 0.0055 1.0000
6.750 1.3377 0.01960 0.01205 -0.1496 0.0053 1.0000
7.000 1.3567 0.02043 0.01301 -0.1480 0.0052 1.0000
7.250 1.3748 0.02136 0.01403 -0.1463 0.0050 1.0000
7.500 1.3919 0.02240 0.01518 -0.1445 0.0049 1.0000
7.750 1.4082 0.02357 0.01647 -0.1425 0.0047 1.0000
8.000 1.4241 0.02488 0.01790 -0.1405 0.0046 1.0000
8.250 1.4397 0.02631 0.01948 -0.1384 0.0045 1.0000
8.500 1.4550 0.02790 0.02122 -0.1364 0.0044 1.0000
8.750 1.4704 0.02965 0.02316 -0.1344 0.0043 1.0000
9.000 1.4855 0.03159 0.02530 -0.1325 0.0043 1.0000
9.250 1.4994 0.03369 0.02763 -0.1303 0.0043 1.0000
9.500 1.5109 0.03606 0.03028 -0.1279 0.0043 1.0000
9.750 1.5190 0.03854 0.03303 -0.1251 0.0043 1.0000
10.000 1.5230 0.04119 0.03596 -0.1217 0.0043 1.0000
10.250 1.5229 0.04404 0.03910 -0.1179 0.0043 1.0000
10.500 1.5202 0.04684 0.04217 -0.1141 0.0043 1.0000
10.750 1.5156 0.04965 0.04524 -0.1105 0.0042 1.0000
11.000 1.5070 0.05301 0.04886 -0.1068 0.0042 1.0000
11.250 1.4981 0.05630 0.05239 -0.1037 0.0041 1.0000
11.500 1.4869 0.05999 0.05631 -0.1010 0.0040 1.0000
11.750 1.4715 0.06448 0.06105 -0.0989 0.0040 1.0000
12.000 1.4540 0.06953 0.06635 -0.0975 0.0040 1.0000
12.250 1.4375 0.07470 0.07172 -0.0971 0.0040 1.0000
12.500 1.4197 0.08050 0.07774 -0.0976 0.0040 1.0000
12.750 1.4008 0.08700 0.08443 -0.0993 0.0039 1.0000
13.000 1.3799 0.09450 0.09213 -0.1022 0.0039 1.0000
13.250 1.3599 0.10274 0.10054 -0.1064 0.0039 1.0000
13.500 1.3324 0.11405 0.11206 -0.1133 0.0041 1.0000
13.750 1.3147 0.12429 0.12245 -0.1202 0.0041 1.0000
14.000 1.2848 0.14057 0.13890 -0.1313 0.0044 1.0000
14.250 1.2553 0.15998 0.15842 -0.1432 0.0046 1.0000
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Polar data table (+)
Polar graphs
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