EPPLER 393 AIRFOIL (e393-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 393 AIRFOIL (e393-il) Reynolds number: 50,000 Max Cl/Cd: 35.28 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e393-il-50000-n5.txt Download as CSV file: xf-e393-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 393 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3147 0.11840 0.11143 -0.0415 1.0000 0.0994
-9.750 -0.3176 0.11526 0.10838 -0.0426 1.0000 0.0971
-9.500 -0.3256 0.10771 0.10087 -0.0468 1.0000 0.0525
-9.250 -0.3216 0.10457 0.09776 -0.0462 1.0000 0.0512
-9.000 -0.3216 0.10149 0.09477 -0.0461 1.0000 0.0499
-8.750 -0.3243 0.09837 0.09175 -0.0461 1.0000 0.0488
-8.500 -0.3293 0.09532 0.08881 -0.0460 1.0000 0.0478
-8.250 -0.3370 0.09236 0.08599 -0.0456 1.0000 0.0470
-8.000 -0.3479 0.08963 0.08341 -0.0449 1.0000 0.0461
-7.750 -0.3634 0.08721 0.08115 -0.0436 1.0000 0.0453
-7.500 -0.3839 0.08499 0.07910 -0.0417 1.0000 0.0447
-7.000 -0.4212 0.07340 0.06762 -0.0514 0.9964 0.0413
-6.750 -0.4025 0.06691 0.06096 -0.0596 0.9860 0.0410
-6.500 -0.3830 0.06058 0.05433 -0.0673 0.9753 0.0408
-6.250 -0.3603 0.05433 0.04761 -0.0746 0.9650 0.0410
-6.000 -0.3331 0.04951 0.04242 -0.0801 0.9569 0.0430
-5.750 -0.3072 0.04656 0.03924 -0.0831 0.9473 0.0457
-5.500 -0.2759 0.04233 0.03441 -0.0873 0.9393 0.0477
-5.250 -0.2422 0.03840 0.02980 -0.0906 0.9319 0.0492
-5.000 -0.2088 0.03533 0.02603 -0.0928 0.9243 0.0518
-4.750 -0.1745 0.03320 0.02361 -0.0950 0.9176 0.0578
-4.500 -0.1426 0.03138 0.02137 -0.0960 0.9100 0.0635
-4.250 -0.1081 0.02973 0.01953 -0.0974 0.9036 0.0718
-4.000 -0.0774 0.02844 0.01805 -0.0980 0.8961 0.0830
-3.750 -0.0431 0.02718 0.01670 -0.0993 0.8897 0.0997
-3.500 -0.0117 0.02605 0.01557 -0.1005 0.8823 0.1283
-3.250 0.0241 0.02469 0.01447 -0.1029 0.8761 0.1973
-3.000 0.0564 0.02344 0.01400 -0.1046 0.8694 0.3474
-2.750 0.0846 0.02314 0.01407 -0.1043 0.8620 0.4877
-2.500 0.1105 0.02314 0.01409 -0.1034 0.8542 0.5701
-2.250 0.1368 0.02312 0.01404 -0.1023 0.8472 0.6296
-2.000 0.1587 0.02315 0.01400 -0.1004 0.8390 0.6760
-1.750 0.1839 0.02308 0.01385 -0.0990 0.8324 0.7192
-1.500 0.2037 0.02310 0.01381 -0.0970 0.8240 0.7577
-1.250 0.2275 0.02296 0.01360 -0.0953 0.8178 0.7958
-1.000 0.2451 0.02295 0.01353 -0.0929 0.8093 0.8342
-0.750 0.2726 0.02273 0.01323 -0.0922 0.8035 0.8797
-0.500 0.3086 0.02267 0.01305 -0.0939 0.7961 0.9415
-0.250 0.3519 0.02262 0.01275 -0.0976 0.7900 1.0000
0.000 0.3817 0.02292 0.01282 -0.0990 0.7823 1.0000
0.250 0.4152 0.02311 0.01279 -0.1007 0.7760 1.0000
0.500 0.4439 0.02345 0.01295 -0.1015 0.7688 1.0000
0.750 0.4747 0.02372 0.01306 -0.1025 0.7622 1.0000
1.000 0.5033 0.02407 0.01328 -0.1031 0.7554 1.0000
1.250 0.5314 0.02444 0.01354 -0.1036 0.7485 1.0000
1.500 0.5614 0.02474 0.01374 -0.1043 0.7424 1.0000
1.750 0.5863 0.02523 0.01416 -0.1043 0.7347 1.0000
2.000 0.6195 0.02542 0.01427 -0.1053 0.7300 1.0000
2.250 0.6395 0.02611 0.01496 -0.1047 0.7210 1.0000
2.500 0.6734 0.02626 0.01506 -0.1056 0.7165 1.0000
2.750 0.6914 0.02706 0.01587 -0.1047 0.7072 1.0000
3.000 0.7246 0.02722 0.01602 -0.1055 0.7025 1.0000
3.250 0.7420 0.02807 0.01694 -0.1046 0.6932 1.0000
3.500 0.7750 0.02823 0.01711 -0.1052 0.6883 1.0000
3.750 0.7917 0.02914 0.01808 -0.1042 0.6789 1.0000
4.000 0.8251 0.02925 0.01823 -0.1048 0.6739 1.0000
4.250 0.8407 0.03020 0.01932 -0.1036 0.6640 1.0000
4.500 0.8758 0.03020 0.01938 -0.1043 0.6591 1.0000
4.750 0.8902 0.03119 0.02048 -0.1029 0.6485 1.0000
5.000 0.9127 0.03178 0.02117 -0.1023 0.6400 1.0000
5.250 0.9419 0.03196 0.02152 -0.1022 0.6324 1.0000
5.500 0.9591 0.03276 0.02245 -0.1009 0.6219 1.0000
5.750 0.9884 0.03287 0.02270 -0.1008 0.6139 1.0000
6.000 1.0126 0.03320 0.02319 -0.1000 0.6040 1.0000
6.250 1.0305 0.03384 0.02399 -0.0986 0.5924 1.0000
6.500 1.0525 0.03417 0.02454 -0.0975 0.5810 1.0000
6.750 1.0794 0.03413 0.02469 -0.0967 0.5699 1.0000
7.000 1.1087 0.03386 0.02460 -0.0960 0.5582 1.0000
7.250 1.1323 0.03382 0.02476 -0.0948 0.5445 1.0000
7.500 1.1490 0.03411 0.02530 -0.0928 0.5288 1.0000
7.750 1.1643 0.03439 0.02579 -0.0906 0.5117 1.0000
8.000 1.1820 0.03443 0.02603 -0.0885 0.4935 1.0000
8.250 1.2037 0.03412 0.02589 -0.0866 0.4739 1.0000
8.500 1.2082 0.03484 0.02679 -0.0833 0.4520 1.0000
8.750 1.2185 0.03518 0.02726 -0.0804 0.4274 1.0000
9.000 1.2270 0.03574 0.02791 -0.0776 0.3995 1.0000
9.250 1.2334 0.03653 0.02880 -0.0747 0.3678 1.0000
9.500 1.2394 0.03750 0.02966 -0.0720 0.3331 1.0000
9.750 1.2404 0.03909 0.03115 -0.0694 0.2982 1.0000
10.000 1.2387 0.04112 0.03298 -0.0669 0.2654 1.0000
10.250 1.2352 0.04358 0.03527 -0.0649 0.2366 1.0000
10.500 1.2308 0.04635 0.03793 -0.0632 0.2102 1.0000
10.750 1.2267 0.04928 0.04079 -0.0619 0.1869 1.0000
11.000 1.2221 0.05240 0.04379 -0.0608 0.1673 1.0000
11.250 1.2189 0.05559 0.04696 -0.0599 0.1479 1.0000
11.500 1.2158 0.05886 0.05021 -0.0592 0.1315 1.0000
11.750 1.2126 0.06226 0.05358 -0.0587 0.1167 1.0000
12.000 1.2103 0.06567 0.05699 -0.0583 0.1036 1.0000
12.250 1.2081 0.06919 0.06054 -0.0580 0.0916 1.0000
12.500 1.2063 0.07278 0.06418 -0.0579 0.0808 1.0000
12.750 1.2046 0.07644 0.06795 -0.0578 0.0718 1.0000
13.000 1.2024 0.08018 0.07168 -0.0581 0.0644 1.0000
13.250 1.2032 0.08388 0.07561 -0.0581 0.0570 1.0000
13.500 1.2016 0.08763 0.07926 -0.0585 0.0520 1.0000
13.750 1.2039 0.09148 0.08351 -0.0586 0.0470 1.0000
14.000 1.2032 0.09543 0.08756 -0.0593 0.0433 1.0000
14.250 1.2030 0.09943 0.09164 -0.0600 0.0404 1.0000
14.500 1.1996 0.10445 0.09704 -0.0613 0.0380 1.0000
14.750 1.1951 0.10963 0.10250 -0.0630 0.0363 1.0000
15.000 1.1897 0.11511 0.10823 -0.0650 0.0352 1.0000
15.250 1.1823 0.12110 0.11444 -0.0676 0.0345 1.0000
15.500 1.1728 0.12771 0.12128 -0.0709 0.0339 1.0000
15.750 1.1606 0.13530 0.12910 -0.0752 0.0337 1.0000
16.000 1.1428 0.14489 0.13894 -0.0811 0.0340 1.0000
16.250 1.1176 0.15787 0.15213 -0.0896 0.0350 1.0000
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