E392 (10.15%) (e392-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E392 (10.15%) (e392-il) Reynolds number: 100,000 Max Cl/Cd: 61.17 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e392-il-100000.txt Download as CSV file: xf-e392-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E392 (10.15%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3175 0.10100 0.09622 -0.0367 1.0000 0.0855
-8.500 -0.3258 0.09914 0.09447 -0.0391 1.0000 0.0883
-8.250 -0.3441 0.09800 0.09351 -0.0417 1.0000 0.0892
-8.000 -0.3271 0.09276 0.08827 -0.0390 1.0000 0.0921
-7.750 -0.3199 0.09011 0.08566 -0.0374 1.0000 0.0953
-7.500 -0.3247 0.08801 0.08367 -0.0366 1.0000 0.0983
-7.250 -0.3407 0.08669 0.08251 -0.0350 1.0000 0.1004
-7.000 -0.3664 0.08610 0.08210 -0.0325 1.0000 0.1017
-6.750 -0.3921 0.08566 0.08182 -0.0299 1.0000 0.1021
-6.500 -0.4162 0.08492 0.08118 -0.0293 1.0000 0.1026
-6.250 -0.3978 0.07936 0.07563 -0.0355 0.9941 0.1058
-6.000 -0.3612 0.07381 0.06994 -0.0483 0.9845 0.1170
-5.750 -0.3372 0.06888 0.06502 -0.0513 0.9763 0.1213
-5.500 -0.3037 0.06294 0.05889 -0.0628 0.9661 0.1343
-5.250 -0.2679 0.05813 0.05390 -0.0707 0.9584 0.1485
-5.000 -0.2418 0.05498 0.05076 -0.0716 0.9496 0.1567
-4.750 -0.1768 0.03932 0.03330 -0.0897 0.9434 0.0750
-4.500 -0.1431 0.03379 0.02705 -0.0920 0.9346 0.0615
-4.250 -0.0997 0.02985 0.02256 -0.0959 0.9299 0.0600
-4.000 -0.0637 0.02780 0.01985 -0.0974 0.9214 0.0622
-3.750 -0.0203 0.02476 0.01639 -0.1002 0.9168 0.0636
-3.500 0.0162 0.02286 0.01439 -0.1017 0.9099 0.0684
-3.250 0.0537 0.02139 0.01281 -0.1033 0.9032 0.0812
-3.000 0.0897 0.01989 0.01142 -0.1046 0.8967 0.1123
-2.750 0.1216 0.01847 0.01043 -0.1055 0.8888 0.1973
-2.500 0.1502 0.01675 0.00999 -0.1060 0.8819 0.4572
-2.250 0.1736 0.01625 0.01002 -0.1042 0.8737 0.6418
-2.000 0.1933 0.01607 0.01006 -0.1013 0.8654 0.7523
-1.750 0.2129 0.01582 0.00993 -0.0978 0.8582 0.8498
-1.500 0.2702 0.01538 0.00935 -0.1021 0.8532 0.9852
-1.250 0.3022 0.01546 0.00912 -0.1037 0.8445 1.0000
-1.000 0.3292 0.01566 0.00908 -0.1040 0.8359 1.0000
-0.750 0.3597 0.01575 0.00893 -0.1046 0.8287 1.0000
-0.500 0.3849 0.01605 0.00905 -0.1045 0.8198 1.0000
-0.250 0.4155 0.01615 0.00896 -0.1049 0.8134 1.0000
0.000 0.4398 0.01652 0.00920 -0.1046 0.8045 1.0000
0.250 0.4702 0.01663 0.00915 -0.1049 0.7985 1.0000
0.500 0.4938 0.01706 0.00949 -0.1045 0.7896 1.0000
0.750 0.5238 0.01718 0.00950 -0.1047 0.7838 1.0000
1.000 0.5471 0.01766 0.00992 -0.1043 0.7749 1.0000
1.250 0.5767 0.01781 0.00997 -0.1044 0.7692 1.0000
1.500 0.5997 0.01833 0.01047 -0.1040 0.7604 1.0000
1.750 0.6291 0.01849 0.01057 -0.1040 0.7548 1.0000
2.000 0.6518 0.01905 0.01113 -0.1036 0.7461 1.0000
2.250 0.6811 0.01922 0.01125 -0.1035 0.7403 1.0000
2.500 0.7035 0.01982 0.01187 -0.1031 0.7317 1.0000
2.750 0.7327 0.01998 0.01203 -0.1030 0.7258 1.0000
3.000 0.7549 0.02060 0.01269 -0.1025 0.7170 1.0000
3.250 0.7845 0.02072 0.01280 -0.1024 0.7111 1.0000
3.500 0.8062 0.02135 0.01350 -0.1018 0.7017 1.0000
3.750 0.8368 0.02137 0.01354 -0.1016 0.6959 1.0000
4.000 0.8581 0.02198 0.01425 -0.1009 0.6857 1.0000
4.250 0.8862 0.02212 0.01441 -0.1005 0.6783 1.0000
4.500 0.9116 0.02238 0.01474 -0.0999 0.6689 1.0000
4.750 0.9353 0.02275 0.01524 -0.0991 0.6589 1.0000
5.000 0.9675 0.02248 0.01498 -0.0988 0.6516 1.0000
5.250 0.9900 0.02280 0.01543 -0.0979 0.6398 1.0000
5.500 1.0148 0.02295 0.01568 -0.0970 0.6284 1.0000
5.750 1.0418 0.02285 0.01570 -0.0961 0.6172 1.0000
6.000 1.0709 0.02255 0.01546 -0.0954 0.6058 1.0000
6.250 1.0997 0.02221 0.01518 -0.0946 0.5933 1.0000
6.500 1.1258 0.02198 0.01508 -0.0935 0.5788 1.0000
6.750 1.1492 0.02182 0.01509 -0.0921 0.5620 1.0000
7.000 1.1727 0.02156 0.01497 -0.0907 0.5433 1.0000
7.250 1.1981 0.02109 0.01459 -0.0893 0.5232 1.0000
7.500 1.2192 0.02081 0.01448 -0.0874 0.4980 1.0000
7.750 1.2387 0.02042 0.01413 -0.0851 0.4642 1.0000
8.000 1.2510 0.02045 0.01412 -0.0820 0.4111 1.0000
8.250 1.2579 0.02116 0.01448 -0.0785 0.3383 1.0000
8.500 1.2588 0.02268 0.01550 -0.0748 0.2658 1.0000
8.750 1.2557 0.02466 0.01705 -0.0709 0.2034 1.0000
9.000 1.2464 0.02694 0.01891 -0.0664 0.1520 1.0000
9.250 1.2329 0.02958 0.02114 -0.0617 0.1141 1.0000
9.500 1.2220 0.03238 0.02369 -0.0578 0.0887 1.0000
9.750 1.2188 0.03489 0.02611 -0.0550 0.0738 1.0000
10.000 1.2208 0.03720 0.02837 -0.0528 0.0650 1.0000
10.250 1.2321 0.03930 0.03052 -0.0509 0.0590 1.0000
10.500 1.2491 0.04133 0.03248 -0.0495 0.0544 1.0000
10.750 1.2811 0.04377 0.03500 -0.0490 0.0504 1.0000
11.000 1.2997 0.04592 0.03737 -0.0480 0.0470 1.0000
11.250 1.3236 0.04855 0.04016 -0.0475 0.0447 1.0000
11.500 1.3527 0.05218 0.04400 -0.0477 0.0433 1.0000
11.750 1.3729 0.05665 0.04880 -0.0475 0.0426 1.0000
12.000 1.3775 0.06068 0.05319 -0.0459 0.0425 1.0000
12.250 1.3743 0.06462 0.05746 -0.0439 0.0424 1.0000
12.500 1.3660 0.06864 0.06180 -0.0420 0.0423 1.0000
12.750 1.3536 0.07294 0.06640 -0.0404 0.0422 1.0000
13.000 1.3383 0.07713 0.07087 -0.0392 0.0422 1.0000
13.250 1.3212 0.08142 0.07543 -0.0386 0.0422 1.0000
13.500 1.3024 0.08588 0.08015 -0.0387 0.0423 1.0000
13.750 1.2819 0.09054 0.08508 -0.0395 0.0426 1.0000
14.500 0.9778 0.11513 0.11116 -0.0487 0.0491 1.0000
14.750 0.9418 0.12488 0.12105 -0.0553 0.0503 1.0000
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Polar data table (+)
Polar graphs
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