E392 (10.15%) (e392-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E392 (10.15%) (e392-il) Reynolds number: 200,000 Max Cl/Cd: 84.62 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e392-il-200000-n5.txt Download as CSV file: xf-e392-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3303 0.08985 0.08642 -0.0409 1.0000 0.0162
-8.500 -0.3270 0.08762 0.08423 -0.0404 1.0000 0.0156
-8.250 -0.3279 0.08469 0.08136 -0.0406 1.0000 0.0151
-8.000 -0.3317 0.08169 0.07844 -0.0408 1.0000 0.0146
-7.750 -0.3341 0.07818 0.07501 -0.0421 0.9964 0.0142
-7.500 -0.3225 0.07195 0.06878 -0.0499 0.9785 0.0134
-7.250 -0.3070 0.05729 0.05408 -0.0703 0.9548 0.0118
-7.000 -0.2866 0.04841 0.04499 -0.0818 0.9356 0.0116
-6.750 -0.2675 0.03952 0.03567 -0.0904 0.9172 0.0114
-6.250 -0.2254 0.02734 0.02204 -0.0975 0.8840 0.0120
-6.000 -0.2007 0.02541 0.01982 -0.0985 0.8691 0.0128
-5.750 -0.1755 0.02332 0.01732 -0.0990 0.8548 0.0134
-5.500 -0.1501 0.02096 0.01443 -0.0990 0.8413 0.0134
-5.250 -0.1243 0.01921 0.01227 -0.0988 0.8283 0.0137
-5.000 -0.0983 0.01783 0.01058 -0.0985 0.8159 0.0141
-4.750 -0.0720 0.01670 0.00920 -0.0982 0.8042 0.0145
-4.500 -0.0457 0.01575 0.00803 -0.0979 0.7933 0.0152
-4.000 0.0074 0.01430 0.00628 -0.0975 0.7726 0.0177
-3.750 0.0344 0.01387 0.00574 -0.0974 0.7632 0.0207
-3.500 0.0615 0.01333 0.00505 -0.0972 0.7544 0.0234
-3.250 0.0889 0.01286 0.00449 -0.0971 0.7454 0.0302
-3.000 0.1163 0.01241 0.00405 -0.0971 0.7374 0.0530
-2.750 0.1434 0.01200 0.00378 -0.0972 0.7291 0.0968
-2.500 0.1705 0.01157 0.00356 -0.0973 0.7217 0.1649
-2.250 0.1977 0.01123 0.00337 -0.0974 0.7141 0.2334
-2.000 0.2248 0.01088 0.00324 -0.0975 0.7073 0.3195
-1.750 0.2515 0.01056 0.00317 -0.0974 0.7001 0.4188
-1.500 0.2781 0.01034 0.00313 -0.0972 0.6939 0.5077
-1.250 0.3046 0.01017 0.00312 -0.0969 0.6869 0.5776
-1.000 0.3306 0.01006 0.00309 -0.0963 0.6811 0.6377
-0.750 0.3561 0.00993 0.00310 -0.0957 0.6745 0.6956
-0.500 0.3806 0.00983 0.00310 -0.0946 0.6686 0.7538
-0.250 0.4036 0.00973 0.00310 -0.0932 0.6629 0.8141
0.000 0.4268 0.00962 0.00306 -0.0917 0.6568 0.8834
0.250 0.4641 0.00952 0.00293 -0.0934 0.6515 0.9897
0.500 0.4925 0.00961 0.00294 -0.0936 0.6452 1.0000
0.750 0.5204 0.00972 0.00295 -0.0937 0.6396 1.0000
1.000 0.5483 0.00983 0.00299 -0.0938 0.6342 1.0000
1.250 0.5761 0.00994 0.00304 -0.0938 0.6281 1.0000
1.500 0.6039 0.01007 0.00309 -0.0939 0.6230 1.0000
1.750 0.6317 0.01019 0.00319 -0.0939 0.6170 1.0000
2.000 0.6593 0.01031 0.00328 -0.0939 0.6113 1.0000
2.250 0.6870 0.01045 0.00337 -0.0939 0.6061 1.0000
2.500 0.7145 0.01058 0.00352 -0.0939 0.5997 1.0000
2.750 0.7421 0.01072 0.00362 -0.0939 0.5942 1.0000
3.000 0.7694 0.01086 0.00377 -0.0939 0.5877 1.0000
3.250 0.7967 0.01099 0.00391 -0.0938 0.5811 1.0000
3.500 0.8238 0.01113 0.00408 -0.0937 0.5736 1.0000
3.750 0.8507 0.01127 0.00421 -0.0936 0.5656 1.0000
4.000 0.8775 0.01141 0.00439 -0.0934 0.5567 1.0000
4.250 0.9042 0.01156 0.00456 -0.0932 0.5481 1.0000
4.500 0.9307 0.01170 0.00474 -0.0930 0.5381 1.0000
4.750 0.9570 0.01185 0.00494 -0.0927 0.5274 1.0000
5.000 0.9830 0.01201 0.00513 -0.0924 0.5161 1.0000
5.250 1.0088 0.01219 0.00536 -0.0921 0.5038 1.0000
5.500 1.0343 0.01237 0.00558 -0.0917 0.4902 1.0000
5.750 1.0594 0.01258 0.00583 -0.0912 0.4744 1.0000
6.000 1.0840 0.01281 0.00609 -0.0907 0.4553 1.0000
6.250 1.1070 0.01312 0.00638 -0.0899 0.4269 1.0000
6.500 1.1276 0.01359 0.00671 -0.0887 0.3837 1.0000
6.750 1.1439 0.01441 0.00720 -0.0870 0.3204 1.0000
7.000 1.1583 0.01546 0.00792 -0.0853 0.2584 1.0000
7.250 1.1730 0.01652 0.00873 -0.0836 0.2091 1.0000
7.500 1.1868 0.01765 0.00963 -0.0819 0.1613 1.0000
7.750 1.1996 0.01882 0.01055 -0.0801 0.1196 1.0000
8.000 1.2124 0.01994 0.01149 -0.0782 0.0871 1.0000
8.250 1.2256 0.02098 0.01242 -0.0764 0.0643 1.0000
8.500 1.2368 0.02209 0.01345 -0.0743 0.0441 1.0000
8.750 1.2456 0.02321 0.01454 -0.0718 0.0311 1.0000
9.000 1.2534 0.02435 0.01568 -0.0692 0.0248 1.0000
9.250 1.2628 0.02542 0.01688 -0.0670 0.0219 1.0000
9.500 1.2701 0.02667 0.01819 -0.0647 0.0199 1.0000
9.750 1.2764 0.02806 0.01967 -0.0625 0.0185 1.0000
10.000 1.2840 0.02940 0.02114 -0.0607 0.0174 1.0000
10.250 1.2906 0.03089 0.02275 -0.0590 0.0165 1.0000
10.500 1.2962 0.03256 0.02454 -0.0574 0.0158 1.0000
10.750 1.3006 0.03441 0.02651 -0.0559 0.0153 1.0000
11.000 1.3040 0.03645 0.02866 -0.0546 0.0149 1.0000
11.250 1.3058 0.03873 0.03107 -0.0535 0.0145 1.0000
11.500 1.3056 0.04132 0.03377 -0.0524 0.0141 1.0000
11.750 1.3062 0.04393 0.03648 -0.0515 0.0138 1.0000
12.000 1.3097 0.04632 0.03901 -0.0507 0.0136 1.0000
12.250 1.3134 0.04878 0.04160 -0.0500 0.0134 1.0000
12.500 1.3171 0.05127 0.04423 -0.0494 0.0132 1.0000
12.750 1.3211 0.05381 0.04693 -0.0489 0.0128 1.0000
13.000 1.3246 0.05645 0.04971 -0.0485 0.0124 1.0000
13.250 1.3275 0.05921 0.05263 -0.0482 0.0120 1.0000
13.500 1.3296 0.06212 0.05569 -0.0481 0.0116 1.0000
13.750 1.3310 0.06520 0.05895 -0.0481 0.0114 1.0000
14.000 1.3316 0.06846 0.06237 -0.0482 0.0111 1.0000
14.250 1.3314 0.07194 0.06601 -0.0484 0.0109 1.0000
14.500 1.3300 0.07566 0.06989 -0.0489 0.0108 1.0000
14.750 1.3272 0.07965 0.07405 -0.0497 0.0106 1.0000
15.000 1.3235 0.08393 0.07851 -0.0507 0.0105 1.0000
15.250 1.3183 0.08855 0.08331 -0.0519 0.0103 1.0000
15.500 1.3117 0.09353 0.08847 -0.0536 0.0102 1.0000
15.750 1.3035 0.09893 0.09405 -0.0556 0.0101 1.0000
16.000 1.2938 0.10477 0.10010 -0.0580 0.0101 1.0000
16.250 1.2828 0.11108 0.10660 -0.0610 0.0100 1.0000
16.500 1.2699 0.11796 0.11368 -0.0645 0.0099 1.0000
16.750 1.2562 0.12534 0.12127 -0.0686 0.0098 1.0000
17.000 1.2422 0.13314 0.12926 -0.0733 0.0098 1.0000
17.250 1.2281 0.14137 0.13768 -0.0786 0.0098 1.0000
17.500 1.2138 0.15014 0.14663 -0.0844 0.0098 1.0000
17.750 1.1989 0.15962 0.15630 -0.0908 0.0099 1.0000
18.000 1.1764 0.17261 0.16953 -0.0996 0.0101 1.0000
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Polar data table (+)
Polar graphs
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