E64 (8.45%) (e64-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E64 (8.45%) (e64-il) Reynolds number: 50,000 Max Cl/Cd: 41.48 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e64-il-50000.txt Download as CSV file: xf-e64-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E64 (8.45%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.4002 0.10075 0.09427 -0.0226 1.0000 0.2290
-7.250 -0.3826 0.09605 0.08957 -0.0210 1.0000 0.2380
-7.000 -0.4136 0.09664 0.09039 -0.0193 1.0000 0.2438
-6.750 -0.3950 0.09201 0.08573 -0.0173 1.0000 0.2545
-6.500 -0.4074 0.09022 0.08409 -0.0156 1.0000 0.2616
-6.250 -0.4218 0.08910 0.08311 -0.0153 1.0000 0.2731
-6.000 -0.4102 0.08537 0.07941 -0.0120 1.0000 0.2847
-5.750 -0.4101 0.08273 0.07685 -0.0100 1.0000 0.2958
-5.500 -0.4129 0.08039 0.07460 -0.0081 1.0000 0.3122
-5.250 -0.4175 0.07826 0.07256 -0.0066 1.0000 0.3295
-5.000 -0.4218 0.07595 0.07034 -0.0053 1.0000 0.3483
-4.750 -0.4152 0.07308 0.06753 -0.0014 1.0000 0.3671
-4.250 -0.3169 0.04645 0.03898 -0.0567 1.0000 0.1279
-4.000 -0.2926 0.04237 0.03473 -0.0580 1.0000 0.1223
-3.750 -0.2544 0.03732 0.02872 -0.0621 1.0000 0.1122
-3.500 -0.2233 0.03395 0.02483 -0.0635 1.0000 0.1095
-3.250 -0.1912 0.03112 0.02142 -0.0646 1.0000 0.1095
-3.000 -0.1600 0.02906 0.01865 -0.0650 1.0000 0.1141
-2.750 -0.1330 0.02731 0.01679 -0.0649 1.0000 0.1266
-2.500 -0.1061 0.02569 0.01499 -0.0643 1.0000 0.1432
-2.250 -0.0798 0.02413 0.01371 -0.0640 1.0000 0.1962
-2.000 -0.0481 0.02160 0.01257 -0.0642 1.0000 0.4377
-1.750 -0.0397 0.02020 0.01253 -0.0582 1.0000 0.6999
-1.500 -0.0395 0.01903 0.01176 -0.0515 1.0000 1.0000
-1.250 -0.0076 0.01930 0.01124 -0.0537 1.0000 1.0000
-1.000 0.0184 0.01962 0.01107 -0.0544 1.0000 1.0000
-0.750 0.0428 0.01999 0.01104 -0.0547 1.0000 1.0000
-0.500 0.0663 0.02040 0.01110 -0.0549 1.0000 1.0000
-0.250 0.0890 0.02084 0.01126 -0.0550 1.0000 1.0000
0.000 0.1111 0.02133 0.01152 -0.0551 1.0000 1.0000
0.250 0.1327 0.02187 0.01184 -0.0551 1.0000 1.0000
0.500 0.1538 0.02245 0.01223 -0.0551 1.0000 1.0000
0.750 0.1745 0.02308 0.01270 -0.0551 1.0000 1.0000
1.000 0.1946 0.02376 0.01326 -0.0551 1.0000 1.0000
1.250 0.2142 0.02449 0.01389 -0.0551 1.0000 1.0000
1.500 0.2334 0.02528 0.01458 -0.0551 1.0000 1.0000
1.750 0.2521 0.02614 0.01537 -0.0552 1.0000 1.0000
2.000 0.2703 0.02705 0.01623 -0.0553 1.0000 1.0000
2.250 0.3033 0.02834 0.01749 -0.0582 0.9922 1.0000
2.500 0.3546 0.02989 0.01903 -0.0643 0.9743 1.0000
2.750 0.4014 0.03117 0.02033 -0.0693 0.9558 1.0000
3.000 0.4457 0.03227 0.02148 -0.0736 0.9366 1.0000
3.250 0.4962 0.03333 0.02264 -0.0786 0.9182 1.0000
3.500 0.5328 0.03412 0.02353 -0.0810 0.8970 1.0000
3.750 0.5812 0.03479 0.02434 -0.0850 0.8770 1.0000
4.000 0.6192 0.03535 0.02509 -0.0870 0.8549 1.0000
4.250 0.6703 0.03552 0.02548 -0.0904 0.8340 1.0000
4.500 0.7076 0.03574 0.02590 -0.0916 0.8103 1.0000
4.750 0.7632 0.03511 0.02562 -0.0944 0.7883 1.0000
5.000 0.8131 0.03419 0.02502 -0.0958 0.7638 1.0000
5.250 0.8664 0.03272 0.02392 -0.0968 0.7377 1.0000
5.500 0.9228 0.03062 0.02225 -0.0972 0.7091 1.0000
5.750 0.9818 0.02803 0.02001 -0.0971 0.6744 1.0000
6.000 1.0199 0.02668 0.01887 -0.0950 0.6293 1.0000
6.250 1.0527 0.02581 0.01800 -0.0923 0.5750 1.0000
6.500 1.0738 0.02589 0.01794 -0.0888 0.5133 1.0000
6.750 1.0912 0.02648 0.01821 -0.0851 0.4463 1.0000
7.000 1.1032 0.02766 0.01906 -0.0813 0.3785 1.0000
7.250 1.1144 0.02930 0.02023 -0.0779 0.3134 1.0000
7.500 1.1236 0.03136 0.02190 -0.0744 0.2510 1.0000
7.750 1.1277 0.03341 0.02354 -0.0708 0.1955 1.0000
8.000 1.1361 0.03596 0.02564 -0.0679 0.1487 1.0000
8.250 1.1582 0.03924 0.02872 -0.0667 0.1185 1.0000
8.500 1.1872 0.04295 0.03265 -0.0663 0.1047 1.0000
8.750 1.2096 0.04617 0.03611 -0.0652 0.0958 1.0000
9.000 1.2250 0.04990 0.04032 -0.0635 0.0907 1.0000
9.250 1.2361 0.05381 0.04479 -0.0613 0.0880 1.0000
9.500 1.2426 0.05807 0.04957 -0.0589 0.0871 1.0000
9.750 1.2427 0.06252 0.05453 -0.0562 0.0870 1.0000
10.000 1.2366 0.06713 0.05961 -0.0534 0.0876 1.0000
10.250 1.2251 0.07176 0.06464 -0.0507 0.0884 1.0000
10.500 1.2083 0.07629 0.06949 -0.0480 0.0893 1.0000
10.750 1.1875 0.08064 0.07407 -0.0455 0.0903 1.0000
11.000 1.1657 0.08535 0.07897 -0.0440 0.0912 1.0000
11.250 1.1453 0.09056 0.08432 -0.0438 0.0921 1.0000
11.500 1.1299 0.09630 0.09016 -0.0445 0.0931 1.0000
11.750 1.1011 0.10289 0.09691 -0.0471 0.0947 1.0000
12.000 1.0164 0.12117 0.11516 -0.0633 0.1029 1.0000
12.250 1.0099 0.12908 0.12304 -0.0669 0.1054 1.0000
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Polar data table (+)
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