EPPLER 593 AIRFOIL (e593-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 593 AIRFOIL (e593-il) Reynolds number: 50,000 Max Cl/Cd: 16.64 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e593-il-50000-n5.txt Download as CSV file: xf-e593-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3417 0.10687 0.10006 -0.0023 0.6507 0.0564
-8.250 -0.3344 0.10327 0.09647 -0.0039 0.6463 0.0547
-7.750 -0.3352 0.09482 0.08807 -0.0111 0.6405 0.0487
-7.500 -0.3322 0.09120 0.08452 -0.0138 0.6367 0.0487
-7.250 -0.3266 0.08754 0.08088 -0.0164 0.6329 0.0485
-7.000 -0.3204 0.08352 0.07687 -0.0198 0.6295 0.0485
-6.750 -0.3122 0.07961 0.07293 -0.0228 0.6264 0.0482
-6.500 -0.3029 0.07540 0.06868 -0.0262 0.6232 0.0479
-6.250 -0.2917 0.07099 0.06424 -0.0298 0.6195 0.0476
-6.000 -0.2792 0.06635 0.05951 -0.0334 0.6162 0.0473
-5.750 -0.2653 0.06135 0.05432 -0.0371 0.6131 0.0473
-5.500 -0.2499 0.05564 0.04827 -0.0408 0.6106 0.0482
-5.250 -0.2318 0.05145 0.04379 -0.0430 0.6077 0.0502
-5.000 -0.2105 0.04880 0.04096 -0.0443 0.6040 0.0530
-4.750 -0.1886 0.04442 0.03607 -0.0461 0.6008 0.0555
-4.500 -0.1656 0.04067 0.03170 -0.0471 0.5977 0.0599
-4.250 -0.1415 0.03881 0.02951 -0.0471 0.5946 0.0653
-4.000 -0.1160 0.03650 0.02669 -0.0474 0.5914 0.0723
-3.750 -0.0884 0.03451 0.02412 -0.0477 0.5876 0.0815
-3.500 -0.0624 0.03355 0.02309 -0.0477 0.5841 0.0906
-3.250 -0.0353 0.03240 0.02165 -0.0476 0.5811 0.1011
-3.000 -0.0080 0.03142 0.02033 -0.0474 0.5784 0.1132
-2.750 0.0200 0.03068 0.01933 -0.0474 0.5753 0.1266
-2.500 0.0485 0.03014 0.01864 -0.0477 0.5716 0.1411
-2.250 0.0768 0.02968 0.01805 -0.0479 0.5681 0.1568
-2.000 0.1049 0.02929 0.01753 -0.0478 0.5651 0.1737
-1.750 0.1328 0.02896 0.01711 -0.0477 0.5627 0.1923
-1.500 0.1603 0.02875 0.01686 -0.0477 0.5601 0.2145
-1.250 0.1878 0.02869 0.01686 -0.0482 0.5565 0.2412
-1.000 0.2143 0.02855 0.01683 -0.0484 0.5531 0.2763
-0.750 0.2395 0.02825 0.01677 -0.0482 0.5502 0.3328
-0.500 0.2899 0.02619 0.01657 -0.0514 0.5474 1.0000
-0.250 0.3157 0.02666 0.01661 -0.0510 0.5454 1.0000
0.000 0.3414 0.02749 0.01724 -0.0516 0.5417 1.0000
0.250 0.3665 0.02824 0.01777 -0.0519 0.5382 1.0000
0.500 0.3912 0.02888 0.01821 -0.0518 0.5350 1.0000
0.750 0.4159 0.02947 0.01859 -0.0515 0.5324 1.0000
1.000 0.4407 0.03004 0.01895 -0.0511 0.5303 1.0000
1.250 0.4645 0.03101 0.01981 -0.0514 0.5272 1.0000
1.500 0.4872 0.03215 0.02092 -0.0521 0.5230 1.0000
1.750 0.5103 0.03306 0.02173 -0.0521 0.5196 1.0000
2.000 0.5338 0.03384 0.02240 -0.0519 0.5168 1.0000
2.250 0.5578 0.03453 0.02297 -0.0514 0.5146 1.0000
2.500 0.5785 0.03584 0.02426 -0.0519 0.5109 1.0000
2.750 0.5971 0.03743 0.02588 -0.0526 0.5060 1.0000
3.000 0.6182 0.03852 0.02692 -0.0525 0.5025 1.0000
3.250 0.6408 0.03934 0.02769 -0.0521 0.4998 1.0000
3.500 0.6649 0.03997 0.02825 -0.0514 0.4977 1.0000
3.750 0.6729 0.04279 0.03119 -0.0529 0.4904 1.0000
4.000 0.6913 0.04411 0.03251 -0.0528 0.4864 1.0000
4.250 0.7138 0.04490 0.03327 -0.0522 0.4835 1.0000
4.750 0.7345 0.04925 0.03773 -0.0530 0.4720 1.0000
5.000 0.7552 0.05019 0.03866 -0.0524 0.4684 1.0000
5.250 0.7809 0.05062 0.03907 -0.0514 0.4660 1.0000
5.500 0.7702 0.05474 0.04329 -0.0529 0.4560 1.0000
5.750 0.7918 0.05556 0.04412 -0.0521 0.4522 1.0000
6.000 0.8142 0.05635 0.04496 -0.0513 0.4490 1.0000
6.750 0.8108 0.06438 0.05309 -0.0512 0.4260 1.0000
7.000 0.8318 0.06522 0.05398 -0.0505 0.4215 1.0000
7.500 0.8428 0.06935 0.05822 -0.0497 0.4077 1.0000
7.750 0.8716 0.06951 0.05845 -0.0487 0.4046 1.0000
8.000 0.8577 0.07324 0.06221 -0.0491 0.3939 1.0000
8.250 0.8857 0.07336 0.06242 -0.0481 0.3903 1.0000
8.500 0.8747 0.07698 0.06608 -0.0485 0.3799 1.0000
8.750 0.9021 0.07707 0.06629 -0.0474 0.3761 1.0000
9.000 0.8933 0.08056 0.06983 -0.0479 0.3655 1.0000
9.250 0.9209 0.08054 0.06993 -0.0468 0.3617 1.0000
9.500 0.9122 0.08411 0.07355 -0.0473 0.3508 1.0000
10.000 0.9318 0.08759 0.07723 -0.0468 0.3361 1.0000
10.250 0.9316 0.09049 0.08022 -0.0472 0.3268 1.0000
10.500 0.9521 0.09095 0.08079 -0.0463 0.3212 1.0000
10.750 0.9485 0.09435 0.08428 -0.0469 0.3110 1.0000
11.000 0.9739 0.09404 0.08413 -0.0457 0.3063 1.0000
11.250 0.9664 0.09811 0.08827 -0.0467 0.2955 1.0000
11.750 0.9866 0.10151 0.09190 -0.0463 0.2802 1.0000
12.000 0.9838 0.10516 0.09564 -0.0472 0.2703 1.0000
12.250 1.0080 0.10461 0.09527 -0.0459 0.2650 1.0000
12.500 1.0001 0.10923 0.09997 -0.0473 0.2544 1.0000
12.750 1.0302 0.10744 0.09837 -0.0454 0.2500 1.0000
13.000 1.0186 0.11286 0.10385 -0.0472 0.2387 1.0000
13.250 1.0165 0.11680 0.10787 -0.0484 0.2295 1.0000
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Polar data table (+)
Polar graphs
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