EPPLER 593 AIRFOIL (e593-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 593 AIRFOIL (e593-il) Reynolds number: 100,000 Max Cl/Cd: 36.31 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e593-il-100000-n5.txt Download as CSV file: xf-e593-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 593 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3539 0.09635 0.09055 -0.0004 0.5638 0.0229
-8.000 -0.3525 0.09234 0.08655 -0.0027 0.5619 0.0232
-7.750 -0.3481 0.08895 0.08318 -0.0045 0.5596 0.0229
-7.500 -0.3465 0.08515 0.07942 -0.0068 0.5572 0.0228
-7.250 -0.3490 0.08119 0.07551 -0.0095 0.5553 0.0231
-7.000 -0.3459 0.07691 0.07125 -0.0132 0.5532 0.0231
-6.750 -0.3404 0.07230 0.06662 -0.0174 0.5513 0.0231
-6.500 -0.3333 0.06675 0.06101 -0.0224 0.5495 0.0232
-6.250 -0.3234 0.06082 0.05496 -0.0273 0.5478 0.0232
-6.000 -0.3113 0.05397 0.04789 -0.0321 0.5463 0.0232
-5.750 -0.2989 0.04478 0.03824 -0.0368 0.5450 0.0231
-5.500 -0.2841 0.03603 0.02859 -0.0398 0.5432 0.0233
-5.250 -0.2631 0.03131 0.02309 -0.0403 0.5405 0.0242
-5.000 -0.2385 0.02958 0.02108 -0.0404 0.5374 0.0254
-4.750 -0.2131 0.02722 0.01809 -0.0401 0.5347 0.0286
-4.500 -0.1871 0.02647 0.01721 -0.0400 0.5322 0.0318
-4.250 -0.1607 0.02494 0.01530 -0.0397 0.5302 0.0356
-4.000 -0.1335 0.02407 0.01419 -0.0395 0.5279 0.0418
-3.750 -0.1060 0.02339 0.01337 -0.0394 0.5252 0.0494
-3.500 -0.0784 0.02290 0.01273 -0.0392 0.5223 0.0583
-3.250 -0.0512 0.02245 0.01223 -0.0391 0.5196 0.0676
-3.000 -0.0239 0.02201 0.01170 -0.0388 0.5172 0.0771
-2.750 0.0034 0.02159 0.01116 -0.0386 0.5151 0.0872
-2.500 0.0307 0.02124 0.01067 -0.0383 0.5132 0.0983
-2.250 0.0586 0.02098 0.01037 -0.0382 0.5108 0.1102
-2.000 0.0861 0.02074 0.01013 -0.0381 0.5083 0.1227
-1.750 0.1135 0.02051 0.00992 -0.0380 0.5058 0.1359
-1.500 0.1406 0.02030 0.00970 -0.0378 0.5034 0.1506
-1.250 0.1678 0.02011 0.00948 -0.0375 0.5012 0.1673
-1.000 0.1949 0.01996 0.00930 -0.0372 0.4993 0.1879
-0.750 0.2220 0.01981 0.00917 -0.0370 0.4976 0.2127
-0.500 0.2496 0.01975 0.00925 -0.0371 0.4953 0.2494
-0.250 0.2771 0.01961 0.00936 -0.0372 0.4929 0.3122
0.000 0.3305 0.01782 0.00944 -0.0416 0.4900 1.0000
0.250 0.3570 0.01808 0.00949 -0.0413 0.4876 1.0000
0.500 0.3835 0.01833 0.00955 -0.0410 0.4855 1.0000
0.750 0.4100 0.01858 0.00962 -0.0406 0.4837 1.0000
1.000 0.4364 0.01885 0.00972 -0.0403 0.4822 1.0000
1.250 0.4629 0.01924 0.01002 -0.0401 0.4803 1.0000
1.500 0.4892 0.01971 0.01048 -0.0402 0.4774 1.0000
1.750 0.5155 0.02013 0.01086 -0.0401 0.4746 1.0000
2.000 0.5417 0.02050 0.01118 -0.0399 0.4721 1.0000
2.250 0.5680 0.02085 0.01147 -0.0397 0.4700 1.0000
2.500 0.5943 0.02121 0.01175 -0.0395 0.4683 1.0000
2.750 0.6206 0.02152 0.01199 -0.0392 0.4667 1.0000
3.000 0.6468 0.02192 0.01233 -0.0390 0.4648 1.0000
3.250 0.6716 0.02269 0.01323 -0.0392 0.4610 1.0000
3.500 0.6969 0.02329 0.01388 -0.0393 0.4581 1.0000
3.750 0.7224 0.02378 0.01437 -0.0391 0.4556 1.0000
4.000 0.7482 0.02414 0.01472 -0.0389 0.4533 1.0000
4.250 0.7743 0.02445 0.01501 -0.0386 0.4515 1.0000
4.500 0.8006 0.02473 0.01525 -0.0382 0.4500 1.0000
4.750 0.8225 0.02594 0.01667 -0.0386 0.4451 1.0000
5.000 0.8463 0.02665 0.01745 -0.0386 0.4414 1.0000
5.250 0.8713 0.02709 0.01795 -0.0383 0.4387 1.0000
5.500 0.8972 0.02732 0.01818 -0.0379 0.4365 1.0000
5.750 0.9238 0.02744 0.01829 -0.0375 0.4348 1.0000
6.000 0.9418 0.02901 0.02013 -0.0379 0.4285 1.0000
6.250 0.9650 0.02960 0.02081 -0.0377 0.4246 1.0000
6.500 0.9907 0.02974 0.02098 -0.0372 0.4220 1.0000
6.750 1.0179 0.02964 0.02090 -0.0366 0.4200 1.0000
7.000 1.0325 0.03141 0.02293 -0.0369 0.4129 1.0000
7.250 1.0557 0.03180 0.02341 -0.0365 0.4089 1.0000
7.500 1.0831 0.03155 0.02321 -0.0358 0.4063 1.0000
7.750 1.1126 0.03102 0.02269 -0.0351 0.4044 1.0000
8.000 1.1189 0.03347 0.02545 -0.0353 0.3947 1.0000
8.250 1.1476 0.03290 0.02494 -0.0345 0.3919 1.0000
8.750 1.1813 0.03456 0.02693 -0.0337 0.3793 1.0000
9.000 1.2139 0.03343 0.02585 -0.0328 0.3765 1.0000
9.250 1.2112 0.03623 0.02891 -0.0327 0.3661 1.0000
9.500 1.2451 0.03486 0.02762 -0.0317 0.3628 1.0000
9.750 1.2313 0.03855 0.03151 -0.0317 0.3514 1.0000
10.000 1.2433 0.03926 0.03231 -0.0310 0.3448 1.0000
10.250 1.2311 0.04277 0.03589 -0.0316 0.3347 1.0000
10.500 1.2081 0.04798 0.04114 -0.0328 0.3216 1.0000
11.000 1.2027 0.05355 0.04683 -0.0332 0.3004 1.0000
11.250 1.2273 0.05287 0.04625 -0.0322 0.2930 1.0000
11.500 1.2247 0.05571 0.04915 -0.0324 0.2815 1.0000
11.750 1.2342 0.05701 0.05050 -0.0321 0.2711 1.0000
12.000 1.2547 0.05681 0.05034 -0.0312 0.2610 1.0000
12.250 1.2732 0.05683 0.05036 -0.0304 0.2496 1.0000
12.500 1.2774 0.05875 0.05227 -0.0302 0.2369 1.0000
12.750 1.2788 0.06106 0.05458 -0.0301 0.2244 1.0000
13.000 1.2796 0.06349 0.05700 -0.0302 0.2123 1.0000
13.250 1.2799 0.06601 0.05951 -0.0302 0.2006 1.0000
13.500 1.2805 0.06856 0.06203 -0.0304 0.1894 1.0000
13.750 1.2813 0.07120 0.06463 -0.0306 0.1786 1.0000
14.000 1.2791 0.07445 0.06791 -0.0313 0.1680 1.0000
14.250 1.2766 0.07789 0.07139 -0.0320 0.1580 1.0000
14.500 1.2758 0.08108 0.07457 -0.0327 0.1487 1.0000
14.750 1.2747 0.08434 0.07781 -0.0334 0.1398 1.0000
15.000 1.2718 0.08813 0.08168 -0.0345 0.1312 1.0000
15.250 1.2705 0.09159 0.08514 -0.0354 0.1233 1.0000
15.500 1.2678 0.09541 0.08900 -0.0366 0.1157 1.0000
15.750 1.2660 0.09916 0.09281 -0.0377 0.1086 1.0000
16.000 1.2639 0.10296 0.09661 -0.0390 0.1021 1.0000
16.250 1.2616 0.10695 0.10071 -0.0404 0.0957 1.0000
16.500 1.2592 0.11092 0.10468 -0.0418 0.0899 1.0000
16.750 1.2571 0.11498 0.10885 -0.0433 0.0844 1.0000
17.000 1.2544 0.11916 0.11307 -0.0450 0.0793 1.0000
17.250 1.2528 0.12317 0.11714 -0.0466 0.0746 1.0000
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Polar data table (+)
Polar graphs
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