E392 (10.15%) (e392-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E392 (10.15%) (e392-il) Reynolds number: 500,000 Max Cl/Cd: 120.6 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e392-il-500000.txt Download as CSV file: xf-e392-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3250 0.08432 0.08223 -0.0397 1.0000 0.0181
-8.000 -0.3283 0.08159 0.07955 -0.0397 1.0000 0.0184
-7.750 -0.3335 0.07900 0.07702 -0.0395 0.9996 0.0186
-7.500 -0.3145 0.07357 0.07159 -0.0474 0.9904 0.0193
-7.250 -0.2920 0.06658 0.06459 -0.0592 0.9776 0.0204
-7.000 -0.2203 0.03240 0.03017 -0.0874 0.9101 0.0220
-6.750 -0.2170 0.02816 0.02576 -0.0889 0.8853 0.0225
-6.500 -0.2066 0.02551 0.02296 -0.0895 0.8638 0.0230
-6.250 -0.1943 0.02247 0.01972 -0.0905 0.8458 0.0236
-6.000 -0.1792 0.01945 0.01647 -0.0916 0.8304 0.0245
-5.750 -0.1622 0.01614 0.01284 -0.0927 0.8169 0.0262
-5.500 -0.1436 0.01945 0.01453 -0.1002 0.8384 0.0156
-5.250 -0.1198 0.01687 0.01151 -0.0999 0.8240 0.0151
-5.000 -0.0942 0.01532 0.00960 -0.0995 0.8106 0.0153
-4.750 -0.0679 0.01427 0.00829 -0.0991 0.7980 0.0156
-4.500 -0.0414 0.01338 0.00717 -0.0988 0.7862 0.0164
-4.250 -0.0152 0.01226 0.00589 -0.0985 0.7754 0.0167
-4.000 0.0112 0.01141 0.00491 -0.0983 0.7654 0.0171
-3.750 0.0383 0.01083 0.00423 -0.0981 0.7557 0.0180
-3.500 0.0658 0.01040 0.00372 -0.0980 0.7466 0.0196
-3.250 0.0935 0.01011 0.00330 -0.0979 0.7383 0.0216
-3.000 0.1214 0.00965 0.00279 -0.0979 0.7297 0.0286
-2.750 0.1490 0.00910 0.00240 -0.0980 0.7224 0.0799
-2.500 0.1767 0.00881 0.00223 -0.0981 0.7145 0.1264
-2.250 0.2043 0.00849 0.00211 -0.0983 0.7076 0.2012
-2.000 0.2316 0.00799 0.00202 -0.0986 0.7004 0.3309
-1.750 0.2589 0.00769 0.00198 -0.0987 0.6942 0.4408
-1.500 0.2865 0.00748 0.00196 -0.0987 0.6872 0.5190
-1.250 0.3139 0.00737 0.00195 -0.0986 0.6812 0.5817
-1.000 0.3413 0.00723 0.00196 -0.0985 0.6749 0.6419
-0.750 0.3682 0.00713 0.00197 -0.0982 0.6688 0.6998
-0.500 0.3946 0.00704 0.00199 -0.0978 0.6631 0.7551
-0.250 0.4199 0.00692 0.00202 -0.0970 0.6571 0.8126
0.000 0.4424 0.00684 0.00204 -0.0955 0.6519 0.8760
0.250 0.4674 0.00670 0.00200 -0.0944 0.6460 0.9547
0.500 0.5029 0.00672 0.00196 -0.0961 0.6402 1.0000
0.750 0.5313 0.00682 0.00198 -0.0963 0.6349 1.0000
1.000 0.5596 0.00688 0.00200 -0.0964 0.6290 1.0000
1.250 0.5878 0.00699 0.00203 -0.0965 0.6237 1.0000
1.500 0.6160 0.00707 0.00208 -0.0966 0.6180 1.0000
1.750 0.6442 0.00715 0.00214 -0.0967 0.6123 1.0000
2.000 0.6722 0.00727 0.00219 -0.0968 0.6070 1.0000
2.250 0.7002 0.00734 0.00226 -0.0968 0.6005 1.0000
2.500 0.7280 0.00745 0.00232 -0.0969 0.5944 1.0000
2.750 0.7559 0.00752 0.00241 -0.0969 0.5872 1.0000
3.000 0.7835 0.00762 0.00247 -0.0969 0.5803 1.0000
3.250 0.8112 0.00770 0.00257 -0.0969 0.5729 1.0000
3.500 0.8387 0.00781 0.00266 -0.0968 0.5657 1.0000
3.750 0.8662 0.00789 0.00276 -0.0968 0.5576 1.0000
4.000 0.8934 0.00802 0.00285 -0.0967 0.5498 1.0000
4.250 0.9208 0.00809 0.00297 -0.0966 0.5406 1.0000
4.500 0.9479 0.00821 0.00311 -0.0965 0.5320 1.0000
4.750 0.9748 0.00833 0.00323 -0.0964 0.5225 1.0000
5.000 1.0018 0.00844 0.00338 -0.0963 0.5118 1.0000
5.250 1.0283 0.00858 0.00352 -0.0961 0.4980 1.0000
5.500 1.0538 0.00876 0.00366 -0.0957 0.4789 1.0000
5.750 1.0794 0.00895 0.00384 -0.0954 0.4567 1.0000
6.000 1.1041 0.00922 0.00405 -0.0949 0.4311 1.0000
6.250 1.1275 0.00961 0.00433 -0.0942 0.3952 1.0000
6.500 1.1488 0.01021 0.00471 -0.0933 0.3451 1.0000
6.750 1.1666 0.01114 0.00529 -0.0920 0.2781 1.0000
7.000 1.1844 0.01210 0.00595 -0.0907 0.2205 1.0000
7.250 1.2016 0.01308 0.00665 -0.0894 0.1683 1.0000
7.500 1.2190 0.01400 0.00734 -0.0880 0.1259 1.0000
7.750 1.2348 0.01502 0.00811 -0.0865 0.0840 1.0000
8.000 1.2456 0.01641 0.00916 -0.0842 0.0369 1.0000
8.250 1.2600 0.01743 0.01010 -0.0822 0.0224 1.0000
8.500 1.2763 0.01825 0.01095 -0.0806 0.0192 1.0000
8.750 1.2907 0.01915 0.01194 -0.0786 0.0176 1.0000
9.000 1.3050 0.01993 0.01281 -0.0767 0.0167 1.0000
9.250 1.3157 0.02076 0.01373 -0.0741 0.0161 1.0000
9.500 1.3249 0.02168 0.01473 -0.0715 0.0154 1.0000
9.750 1.3329 0.02269 0.01582 -0.0690 0.0147 1.0000
10.000 1.3377 0.02398 0.01717 -0.0662 0.0140 1.0000
10.250 1.3387 0.02561 0.01891 -0.0634 0.0136 1.0000
10.500 1.3351 0.02778 0.02119 -0.0604 0.0132 1.0000
10.750 1.3365 0.02975 0.02329 -0.0583 0.0129 1.0000
11.000 1.3437 0.03133 0.02497 -0.0568 0.0127 1.0000
11.250 1.3488 0.03320 0.02695 -0.0553 0.0126 1.0000
11.500 1.3548 0.03508 0.02893 -0.0540 0.0124 1.0000
11.750 1.3604 0.03708 0.03105 -0.0527 0.0122 1.0000
12.000 1.3664 0.03911 0.03319 -0.0516 0.0119 1.0000
12.250 1.3724 0.04121 0.03540 -0.0506 0.0116 1.0000
12.500 1.3785 0.04331 0.03760 -0.0498 0.0112 1.0000
12.750 1.3838 0.04548 0.03986 -0.0491 0.0108 1.0000
13.000 1.3883 0.04785 0.04234 -0.0485 0.0105 1.0000
13.250 1.3920 0.05041 0.04503 -0.0479 0.0103 1.0000
13.500 1.3950 0.05313 0.04785 -0.0474 0.0100 1.0000
13.750 1.3972 0.05605 0.05090 -0.0469 0.0099 1.0000
14.000 1.3978 0.05940 0.05439 -0.0464 0.0097 1.0000
14.250 1.3960 0.06326 0.05843 -0.0461 0.0095 1.0000
14.500 1.3901 0.06778 0.06316 -0.0460 0.0094 1.0000
14.750 1.3814 0.07267 0.06828 -0.0465 0.0094 1.0000
15.000 1.3698 0.07801 0.07384 -0.0475 0.0094 1.0000
15.250 1.3567 0.08366 0.07970 -0.0490 0.0093 1.0000
15.500 1.3415 0.08987 0.08612 -0.0511 0.0093 1.0000
15.750 1.3253 0.09645 0.09291 -0.0537 0.0093 1.0000
16.000 1.3093 0.10330 0.09996 -0.0569 0.0093 1.0000
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Polar data table (+)
Polar graphs
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