E392 (10.15%) (e392-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E392 (10.15%) (e392-il) Reynolds number: 1,000,000 Max Cl/Cd: 134.01 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e392-il-1000000-n5.txt Download as CSV file: xf-e392-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3456 0.09809 0.09646 -0.0350 1.0000 0.0051
-9.500 -0.3431 0.09471 0.09309 -0.0360 0.9902 0.0049
-8.500 -0.4508 0.02461 0.02146 -0.0961 0.8230 0.0035
-8.250 -0.4353 0.02161 0.01802 -0.0964 0.8051 0.0036
-8.000 -0.4150 0.01970 0.01578 -0.0964 0.7896 0.0036
-7.750 -0.3926 0.01826 0.01407 -0.0964 0.7756 0.0037
-7.500 -0.3689 0.01704 0.01260 -0.0963 0.7627 0.0038
-7.250 -0.3444 0.01603 0.01136 -0.0963 0.7508 0.0039
-6.750 -0.2935 0.01431 0.00923 -0.0962 0.7290 0.0042
-6.500 -0.2674 0.01356 0.00830 -0.0961 0.7194 0.0044
-6.000 -0.2142 0.01230 0.00674 -0.0961 0.7015 0.0048
-5.750 -0.1873 0.01180 0.00611 -0.0960 0.6933 0.0050
-5.500 -0.1600 0.01135 0.00553 -0.0960 0.6852 0.0051
-5.250 -0.1327 0.01095 0.00502 -0.0960 0.6781 0.0052
-5.000 -0.1052 0.01059 0.00457 -0.0960 0.6707 0.0053
-4.750 -0.0778 0.01007 0.00395 -0.0961 0.6642 0.0055
-4.500 -0.0501 0.00963 0.00342 -0.0961 0.6578 0.0060
-4.000 0.0057 0.00913 0.00281 -0.0962 0.6455 0.0069
-3.750 0.0338 0.00890 0.00251 -0.0963 0.6395 0.0073
-3.500 0.0620 0.00871 0.00225 -0.0964 0.6343 0.0078
-3.250 0.0902 0.00856 0.00204 -0.0964 0.6284 0.0082
-3.000 0.1184 0.00838 0.00180 -0.0965 0.6230 0.0095
-2.750 0.1468 0.00823 0.00163 -0.0966 0.6183 0.0111
-2.500 0.1751 0.00804 0.00147 -0.0967 0.6129 0.0231
-2.000 0.2316 0.00771 0.00126 -0.0970 0.6030 0.0675
-1.750 0.2599 0.00759 0.00117 -0.0971 0.5979 0.0914
-1.500 0.2880 0.00740 0.00111 -0.0973 0.5930 0.1391
-1.250 0.3163 0.00718 0.00106 -0.0975 0.5883 0.1992
-1.000 0.3446 0.00701 0.00102 -0.0977 0.5833 0.2512
-0.750 0.3727 0.00687 0.00099 -0.0979 0.5785 0.3080
-0.500 0.4010 0.00666 0.00098 -0.0981 0.5738 0.3853
-0.250 0.4292 0.00654 0.00098 -0.0983 0.5687 0.4383
0.000 0.4573 0.00647 0.00100 -0.0984 0.5639 0.4848
0.250 0.4857 0.00639 0.00102 -0.0986 0.5591 0.5280
0.500 0.5139 0.00633 0.00105 -0.0987 0.5538 0.5697
0.750 0.5419 0.00630 0.00108 -0.0987 0.5489 0.6080
1.000 0.5701 0.00624 0.00113 -0.0988 0.5437 0.6469
1.250 0.5979 0.00620 0.00118 -0.0989 0.5380 0.6894
1.500 0.6255 0.00615 0.00124 -0.0988 0.5323 0.7359
1.750 0.6527 0.00610 0.00131 -0.0987 0.5248 0.7858
2.000 0.6787 0.00604 0.00138 -0.0982 0.5169 0.8418
2.250 0.7020 0.00597 0.00145 -0.0971 0.5082 0.9050
2.500 0.7311 0.00591 0.00147 -0.0972 0.4998 1.0000
2.750 0.7589 0.00602 0.00153 -0.0973 0.4908 1.0000
3.000 0.7868 0.00613 0.00160 -0.0973 0.4806 1.0000
3.250 0.8145 0.00624 0.00169 -0.0974 0.4700 1.0000
3.500 0.8420 0.00638 0.00179 -0.0974 0.4584 1.0000
3.750 0.8694 0.00653 0.00189 -0.0973 0.4452 1.0000
4.000 0.8965 0.00669 0.00201 -0.0973 0.4309 1.0000
4.250 0.9228 0.00695 0.00217 -0.0971 0.4070 1.0000
4.500 0.9481 0.00730 0.00236 -0.0968 0.3707 1.0000
4.750 0.9716 0.00785 0.00266 -0.0963 0.3180 1.0000
5.000 0.9927 0.00865 0.00310 -0.0955 0.2483 1.0000
5.250 1.0152 0.00929 0.00350 -0.0948 0.1993 1.0000
5.500 1.0386 0.00982 0.00386 -0.0943 0.1637 1.0000
5.750 1.0609 0.01045 0.00427 -0.0936 0.1239 1.0000
6.000 1.0839 0.01097 0.00465 -0.0930 0.0959 1.0000
6.250 1.1070 0.01148 0.00505 -0.0924 0.0730 1.0000
6.500 1.1297 0.01200 0.00546 -0.0918 0.0528 1.0000
6.750 1.1517 0.01257 0.00592 -0.0910 0.0340 1.0000
7.000 1.1720 0.01328 0.00650 -0.0900 0.0135 1.0000
7.250 1.1950 0.01371 0.00694 -0.0894 0.0105 1.0000
7.500 1.2184 0.01408 0.00733 -0.0888 0.0095 1.0000
7.750 1.2415 0.01447 0.00775 -0.0881 0.0090 1.0000
8.000 1.2640 0.01488 0.00820 -0.0874 0.0085 1.0000
8.250 1.2859 0.01533 0.00868 -0.0866 0.0082 1.0000
8.500 1.3070 0.01581 0.00921 -0.0857 0.0078 1.0000
8.750 1.3272 0.01634 0.00978 -0.0847 0.0075 1.0000
9.000 1.3463 0.01692 0.01041 -0.0835 0.0072 1.0000
9.250 1.3634 0.01760 0.01116 -0.0820 0.0068 1.0000
9.500 1.3799 0.01828 0.01190 -0.0804 0.0066 1.0000
9.750 1.3967 0.01882 0.01249 -0.0789 0.0065 1.0000
10.000 1.4102 0.01942 0.01315 -0.0768 0.0063 1.0000
10.250 1.4221 0.02009 0.01389 -0.0745 0.0062 1.0000
10.500 1.4333 0.02082 0.01469 -0.0723 0.0061 1.0000
10.750 1.4435 0.02166 0.01559 -0.0700 0.0059 1.0000
11.000 1.4530 0.02258 0.01658 -0.0679 0.0058 1.0000
11.250 1.4619 0.02359 0.01766 -0.0659 0.0057 1.0000
11.500 1.4696 0.02475 0.01891 -0.0639 0.0055 1.0000
11.750 1.4771 0.02600 0.02023 -0.0621 0.0054 1.0000
12.000 1.4843 0.02735 0.02167 -0.0605 0.0053 1.0000
12.250 1.4915 0.02878 0.02318 -0.0590 0.0052 1.0000
12.500 1.4990 0.03025 0.02472 -0.0578 0.0050 1.0000
12.750 1.5057 0.03187 0.02641 -0.0567 0.0049 1.0000
13.000 1.5109 0.03371 0.02832 -0.0557 0.0048 1.0000
13.250 1.5135 0.03586 0.03057 -0.0547 0.0047 1.0000
13.500 1.5138 0.03835 0.03315 -0.0538 0.0045 1.0000
13.750 1.5120 0.04115 0.03606 -0.0531 0.0044 1.0000
14.000 1.5055 0.04461 0.03964 -0.0525 0.0043 1.0000
14.250 1.5107 0.04683 0.04195 -0.0523 0.0043 1.0000
14.500 1.5139 0.04933 0.04454 -0.0522 0.0042 1.0000
14.750 1.5165 0.05199 0.04731 -0.0522 0.0042 1.0000
15.000 1.5203 0.05458 0.04999 -0.0523 0.0041 1.0000
15.250 1.5231 0.05734 0.05285 -0.0525 0.0040 1.0000
15.500 1.5219 0.06074 0.05636 -0.0530 0.0039 1.0000
15.750 1.5206 0.06427 0.06000 -0.0536 0.0038 1.0000
16.000 1.5191 0.06794 0.06378 -0.0544 0.0037 1.0000
16.250 1.5162 0.07191 0.06786 -0.0554 0.0037 1.0000
16.500 1.5133 0.07601 0.07207 -0.0565 0.0036 1.0000
16.750 1.5087 0.08050 0.07667 -0.0580 0.0035 1.0000
17.000 1.5047 0.08503 0.08131 -0.0595 0.0035 1.0000
17.250 1.4980 0.09010 0.08649 -0.0614 0.0034 1.0000
17.500 1.4915 0.09531 0.09182 -0.0635 0.0034 1.0000
17.750 1.4844 0.10073 0.09736 -0.0658 0.0033 1.0000
18.000 1.4773 0.10629 0.10303 -0.0683 0.0033 1.0000
18.250 1.4684 0.11228 0.10914 -0.0712 0.0032 1.0000
18.500 1.4603 0.11826 0.11523 -0.0741 0.0032 1.0000
18.750 1.4516 0.12449 0.12157 -0.0774 0.0031 1.0000
19.000 1.4411 0.13120 0.12840 -0.0810 0.0031 1.0000
19.250 1.4311 0.13789 0.13520 -0.0847 0.0031 1.0000
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Polar data table (+)
Polar graphs
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