EPPLER 545 AIRFOIL (e545-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 545 AIRFOIL (e545-il) Reynolds number: 200,000 Max Cl/Cd: 63.61 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e545-il-200000-n5.txt Download as CSV file: xf-e545-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 545 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5114 0.09918 0.09533 -0.0572 1.0000 0.0081
-13.750 -0.5444 0.08674 0.08274 -0.0645 1.0000 0.0080
-13.500 -0.5690 0.07854 0.07439 -0.0691 1.0000 0.0079
-13.250 -0.5944 0.07155 0.06722 -0.0722 1.0000 0.0078
-13.000 -0.6169 0.06593 0.06142 -0.0739 1.0000 0.0077
-12.750 -0.6362 0.06126 0.05656 -0.0746 1.0000 0.0077
-12.500 -0.6539 0.05710 0.05221 -0.0745 1.0000 0.0077
-12.250 -0.6692 0.05345 0.04837 -0.0739 1.0000 0.0076
-12.000 -0.6831 0.05013 0.04484 -0.0726 1.0000 0.0076
-11.750 -0.6953 0.04708 0.04157 -0.0709 1.0000 0.0076
-11.500 -0.7032 0.04465 0.03895 -0.0689 1.0000 0.0076
-11.250 -0.7108 0.04233 0.03643 -0.0664 1.0000 0.0076
-11.000 -0.7164 0.04046 0.03440 -0.0636 1.0000 0.0077
-10.750 -0.7026 0.03788 0.03153 -0.0644 0.9963 0.0078
-10.500 -0.6813 0.03544 0.02880 -0.0656 0.9889 0.0080
-10.250 -0.6586 0.03358 0.02673 -0.0666 0.9795 0.0081
-10.000 -0.6359 0.03186 0.02478 -0.0671 0.9687 0.0084
-9.750 -0.6116 0.03038 0.02317 -0.0680 0.9587 0.0085
-9.500 -0.5852 0.02898 0.02171 -0.0696 0.9499 0.0088
-9.250 -0.5557 0.02765 0.02029 -0.0717 0.9416 0.0094
-9.000 -0.5247 0.02631 0.01883 -0.0740 0.9329 0.0102
-8.750 -0.4919 0.02506 0.01743 -0.0767 0.9239 0.0106
-8.500 -0.4618 0.02383 0.01614 -0.0792 0.9123 0.0113
-8.250 -0.4303 0.02277 0.01496 -0.0816 0.9007 0.0123
-8.000 -0.4009 0.02182 0.01392 -0.0836 0.8882 0.0150
-7.750 -0.3781 0.02093 0.01296 -0.0842 0.8743 0.0175
-7.500 -0.3591 0.02008 0.01203 -0.0840 0.8606 0.0202
-7.250 -0.3428 0.01930 0.01116 -0.0832 0.8479 0.0246
-7.000 -0.3323 0.01855 0.01039 -0.0813 0.8348 0.0316
-6.750 -0.3259 0.01791 0.00974 -0.0785 0.8229 0.0410
-6.500 -0.3157 0.01726 0.00911 -0.0764 0.8130 0.0574
-6.250 -0.3071 0.01659 0.00854 -0.0739 0.8024 0.0842
-6.000 -0.2968 0.01584 0.00794 -0.0718 0.7935 0.1246
-5.750 -0.2893 0.01494 0.00733 -0.0693 0.7838 0.1860
-5.500 -0.2845 0.01367 0.00652 -0.0667 0.7757 0.2950
-5.250 -0.2819 0.01244 0.00628 -0.0632 0.7670 0.4789
-5.000 -0.2565 0.01272 0.00663 -0.0624 0.7603 0.5569
-4.750 -0.2297 0.01297 0.00678 -0.0620 0.7537 0.5796
-4.500 -0.2030 0.01320 0.00688 -0.0616 0.7464 0.5957
-4.250 -0.1757 0.01351 0.00703 -0.0613 0.7401 0.6105
-4.000 -0.1494 0.01394 0.00736 -0.0607 0.7333 0.6259
-3.750 -0.1208 0.01472 0.00817 -0.0597 0.7269 0.6364
-3.500 -0.0942 0.01478 0.00805 -0.0596 0.7215 0.6448
-3.250 -0.0671 0.01478 0.00798 -0.0595 0.7153 0.6466
-3.000 -0.0400 0.01473 0.00783 -0.0594 0.7090 0.6483
-2.750 -0.0124 0.01468 0.00766 -0.0595 0.7036 0.6501
-2.500 0.0146 0.01460 0.00750 -0.0596 0.6977 0.6520
-2.250 0.0415 0.01451 0.00732 -0.0597 0.6919 0.6539
-2.000 0.0690 0.01442 0.00711 -0.0599 0.6865 0.6561
-1.750 0.0961 0.01431 0.00689 -0.0601 0.6804 0.6580
-1.500 0.1229 0.01419 0.00667 -0.0603 0.6735 0.6600
-1.250 0.1507 0.01409 0.00642 -0.0607 0.6675 0.6622
-1.000 0.1776 0.01404 0.00634 -0.0607 0.6612 0.6634
-0.750 0.2045 0.01400 0.00625 -0.0607 0.6548 0.6644
-0.500 0.2321 0.01397 0.00616 -0.0608 0.6495 0.6655
-0.250 0.2593 0.01395 0.00610 -0.0609 0.6443 0.6667
0.000 0.2863 0.01393 0.00607 -0.0610 0.6391 0.6679
0.250 0.3138 0.01392 0.00602 -0.0612 0.6344 0.6694
0.500 0.3418 0.01394 0.00597 -0.0614 0.6301 0.6711
0.750 0.3687 0.01393 0.00597 -0.0615 0.6250 0.6729
1.000 0.3958 0.01392 0.00595 -0.0617 0.6200 0.6744
1.250 0.4235 0.01392 0.00591 -0.0619 0.6154 0.6760
1.500 0.4517 0.01394 0.00587 -0.0623 0.6113 0.6776
1.750 0.4784 0.01394 0.00589 -0.0624 0.6057 0.6793
2.000 0.5055 0.01395 0.00588 -0.0625 0.6001 0.6808
2.250 0.5328 0.01398 0.00589 -0.0626 0.5952 0.6819
2.500 0.5593 0.01402 0.00597 -0.0626 0.5901 0.6832
2.750 0.5855 0.01406 0.00609 -0.0625 0.5848 0.6847
3.000 0.6122 0.01412 0.00615 -0.0624 0.5796 0.6863
3.250 0.6390 0.01418 0.00622 -0.0624 0.5743 0.6880
3.500 0.6644 0.01423 0.00634 -0.0622 0.5674 0.6896
3.750 0.6907 0.01428 0.00640 -0.0621 0.5612 0.6913
4.000 0.7167 0.01434 0.00649 -0.0620 0.5548 0.6931
4.250 0.7419 0.01440 0.00660 -0.0618 0.5469 0.6949
4.500 0.7680 0.01447 0.00665 -0.0617 0.5401 0.6967
4.750 0.7924 0.01454 0.00679 -0.0613 0.5312 0.6986
5.000 0.8174 0.01462 0.00689 -0.0610 0.5237 0.7001
5.250 0.8412 0.01471 0.00709 -0.0604 0.5156 0.7016
5.500 0.8653 0.01481 0.00724 -0.0599 0.5079 0.7034
5.750 0.8888 0.01493 0.00746 -0.0593 0.4996 0.7055
6.000 0.9119 0.01505 0.00763 -0.0586 0.4904 0.7077
6.250 0.9344 0.01518 0.00785 -0.0579 0.4800 0.7100
6.500 0.9563 0.01534 0.00805 -0.0570 0.4692 0.7123
6.750 0.9776 0.01550 0.00827 -0.0561 0.4571 0.7146
7.000 0.9975 0.01569 0.00850 -0.0549 0.4422 0.7169
7.250 1.0133 0.01593 0.00874 -0.0529 0.4219 0.7189
7.500 1.0265 0.01623 0.00903 -0.0505 0.3982 0.7210
7.750 1.0346 0.01661 0.00935 -0.0472 0.3731 0.7233
8.000 1.0413 0.01710 0.00978 -0.0438 0.3486 0.7260
8.250 1.0475 0.01773 0.01034 -0.0405 0.3244 0.7288
8.500 1.0529 0.01846 0.01099 -0.0372 0.3028 0.7319
8.750 1.0596 0.01922 0.01170 -0.0344 0.2830 0.7353
9.000 1.0655 0.02000 0.01249 -0.0315 0.2657 0.7382
9.250 1.0713 0.02085 0.01334 -0.0288 0.2491 0.7414
9.500 1.0767 0.02179 0.01428 -0.0263 0.2334 0.7449
9.750 1.0810 0.02285 0.01532 -0.0238 0.2188 0.7486
10.250 1.0918 0.02509 0.01759 -0.0197 0.1955 0.7559
10.500 1.0992 0.02617 0.01874 -0.0179 0.1832 0.7596
10.750 1.1072 0.02728 0.01992 -0.0164 0.1639 0.7639
11.000 1.1068 0.02898 0.02149 -0.0144 0.1346 0.7686
11.250 1.1061 0.03082 0.02325 -0.0126 0.1220 0.7732
11.500 1.1069 0.03262 0.02508 -0.0110 0.1132 0.7780
11.750 1.1119 0.03423 0.02676 -0.0099 0.1042 0.7838
12.000 1.1179 0.03583 0.02844 -0.0089 0.0952 0.7902
12.250 1.1228 0.03752 0.03021 -0.0080 0.0863 0.7970
12.500 1.1273 0.03933 0.03208 -0.0071 0.0779 0.8050
12.750 1.1309 0.04123 0.03404 -0.0064 0.0703 0.8137
13.000 1.1339 0.04327 0.03614 -0.0057 0.0636 0.8244
13.250 1.1359 0.04540 0.03835 -0.0050 0.0578 0.8371
13.500 1.1379 0.04757 0.04063 -0.0044 0.0524 0.8550
13.750 1.1403 0.04967 0.04291 -0.0038 0.0477 0.8888
14.000 1.1415 0.05190 0.04527 -0.0037 0.0436 1.0000
14.250 1.1432 0.05455 0.04796 -0.0038 0.0400 1.0000
14.500 1.1457 0.05719 0.05065 -0.0041 0.0366 1.0000
14.750 1.1479 0.05992 0.05345 -0.0044 0.0336 1.0000
15.000 1.1486 0.06288 0.05646 -0.0048 0.0311 1.0000
15.250 1.1502 0.06582 0.05949 -0.0053 0.0285 1.0000
15.500 1.1506 0.06896 0.06270 -0.0059 0.0264 1.0000
15.750 1.1508 0.07220 0.06603 -0.0066 0.0246 1.0000
16.000 1.1503 0.07561 0.06953 -0.0075 0.0228 1.0000
16.250 1.1492 0.07918 0.07318 -0.0085 0.0212 1.0000
16.500 1.1480 0.08286 0.07696 -0.0096 0.0197 1.0000
16.750 1.1460 0.08671 0.08092 -0.0109 0.0185 1.0000
17.000 1.1429 0.09083 0.08513 -0.0124 0.0173 1.0000
17.250 1.1400 0.09499 0.08942 -0.0140 0.0163 1.0000
17.500 1.1364 0.09936 0.09388 -0.0158 0.0154 1.0000
17.750 1.1323 0.10387 0.09851 -0.0177 0.0146 1.0000
18.000 1.1278 0.10855 0.10331 -0.0198 0.0138 1.0000
18.250 1.1229 0.11335 0.10822 -0.0221 0.0131 1.0000
18.500 1.1164 0.11851 0.11347 -0.0247 0.0127 1.0000
18.750 1.1120 0.12334 0.11846 -0.0271 0.0120 1.0000
19.000 1.1065 0.12846 0.12370 -0.0298 0.0115 1.0000
19.250 1.1010 0.13362 0.12896 -0.0327 0.0111 1.0000
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Polar data table (+)
Polar graphs
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