EPPLER 545 AIRFOIL (e545-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 545 AIRFOIL (e545-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.04 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e545-il-1000000-n5.txt Download as CSV file: xf-e545-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6965 0.10565 0.10344 -0.0485 1.0000 0.0026
-16.500 -0.7248 0.09492 0.09257 -0.0540 1.0000 0.0026
-16.250 -0.7630 0.08296 0.08038 -0.0606 1.0000 0.0026
-16.000 -0.7839 0.07539 0.07265 -0.0645 1.0000 0.0025
-15.750 -0.8020 0.06893 0.06604 -0.0675 1.0000 0.0025
-15.500 -0.8157 0.06368 0.06066 -0.0695 1.0000 0.0025
-15.250 -0.8285 0.05894 0.05577 -0.0709 1.0000 0.0025
-15.000 -0.8436 0.05427 0.05093 -0.0718 1.0000 0.0025
-14.750 -0.8492 0.05100 0.04755 -0.0721 1.0000 0.0025
-14.500 -0.8567 0.04769 0.04410 -0.0721 1.0000 0.0025
-14.250 -0.8624 0.04477 0.04105 -0.0718 1.0000 0.0025
-14.000 -0.8638 0.04246 0.03863 -0.0712 1.0000 0.0025
-13.750 -0.8671 0.04006 0.03611 -0.0703 1.0000 0.0025
-13.500 -0.8661 0.03816 0.03411 -0.0694 1.0000 0.0025
-13.250 -0.8675 0.03608 0.03191 -0.0680 1.0000 0.0025
-13.000 -0.8579 0.03407 0.02978 -0.0686 0.9993 0.0025
-12.750 -0.8404 0.03208 0.02767 -0.0705 0.9977 0.0025
-12.500 -0.8241 0.03029 0.02576 -0.0717 0.9937 0.0025
-12.250 -0.8149 0.02882 0.02420 -0.0709 0.9854 0.0025
-12.000 -0.8020 0.02741 0.02271 -0.0707 0.9634 0.0025
-11.750 -0.7658 0.02564 0.02080 -0.0755 0.9513 0.0026
-11.500 -0.7202 0.02409 0.01912 -0.0819 0.9401 0.0026
-11.250 -0.6636 0.02251 0.01739 -0.0906 0.9280 0.0026
-11.000 -0.6128 0.02120 0.01591 -0.0979 0.9082 0.0026
-10.750 -0.5849 0.02033 0.01486 -0.0999 0.8786 0.0026
-10.500 -0.5712 0.01962 0.01398 -0.0989 0.8538 0.0027
-10.250 -0.5582 0.01902 0.01326 -0.0974 0.8345 0.0027
-10.000 -0.5469 0.01832 0.01245 -0.0958 0.8184 0.0027
-9.750 -0.5337 0.01773 0.01178 -0.0943 0.8055 0.0027
-9.500 -0.5212 0.01713 0.01108 -0.0927 0.7935 0.0027
-9.250 -0.5085 0.01652 0.01039 -0.0910 0.7822 0.0028
-9.000 -0.4958 0.01594 0.00973 -0.0893 0.7718 0.0028
-8.750 -0.4819 0.01544 0.00917 -0.0878 0.7610 0.0028
-8.500 -0.4686 0.01493 0.00859 -0.0861 0.7519 0.0029
-8.250 -0.4559 0.01443 0.00804 -0.0843 0.7425 0.0029
-8.000 -0.4469 0.01384 0.00738 -0.0818 0.7346 0.0030
-7.750 -0.4404 0.01338 0.00685 -0.0786 0.7262 0.0031
-7.500 -0.4282 0.01305 0.00646 -0.0763 0.7189 0.0034
-7.250 -0.4108 0.01273 0.00610 -0.0749 0.7113 0.0035
-7.000 -0.3928 0.01245 0.00575 -0.0735 0.7033 0.0039
-6.750 -0.3728 0.01218 0.00544 -0.0724 0.6942 0.0043
-6.500 -0.3532 0.01192 0.00512 -0.0713 0.6848 0.0052
-6.250 -0.3315 0.01166 0.00484 -0.0705 0.6780 0.0066
-6.000 -0.3094 0.01142 0.00457 -0.0698 0.6706 0.0082
-5.750 -0.2872 0.01117 0.00431 -0.0691 0.6646 0.0123
-5.500 -0.2640 0.01091 0.00407 -0.0686 0.6590 0.0184
-5.250 -0.2408 0.01067 0.00383 -0.0681 0.6525 0.0272
-5.000 -0.2173 0.01043 0.00361 -0.0676 0.6463 0.0381
-4.750 -0.1941 0.01010 0.00336 -0.0672 0.6409 0.0612
-4.500 -0.1714 0.00973 0.00311 -0.0667 0.6344 0.0954
-4.250 -0.1513 0.00910 0.00276 -0.0660 0.6286 0.1706
-4.000 -0.1313 0.00827 0.00235 -0.0654 0.6221 0.2823
-3.750 -0.1142 0.00691 0.00172 -0.0647 0.6160 0.4791
-3.500 -0.0878 0.00670 0.00167 -0.0647 0.6105 0.5418
-3.250 -0.0592 0.00669 0.00167 -0.0650 0.6057 0.5607
-3.000 -0.0306 0.00672 0.00166 -0.0652 0.6006 0.5749
-2.750 -0.0023 0.00678 0.00170 -0.0654 0.5953 0.5867
-2.500 0.0263 0.00684 0.00174 -0.0657 0.5906 0.5960
-2.250 0.0551 0.00688 0.00176 -0.0659 0.5855 0.6004
-2.000 0.0837 0.00690 0.00173 -0.0662 0.5803 0.6018
-1.750 0.1121 0.00694 0.00170 -0.0665 0.5757 0.6030
-1.500 0.1410 0.00694 0.00167 -0.0668 0.5714 0.6040
-1.250 0.1697 0.00696 0.00165 -0.0671 0.5661 0.6050
-1.000 0.1979 0.00700 0.00164 -0.0673 0.5605 0.6059
-0.750 0.2265 0.00703 0.00163 -0.0676 0.5559 0.6067
-0.500 0.2552 0.00706 0.00162 -0.0680 0.5509 0.6074
-0.250 0.2835 0.00709 0.00162 -0.0682 0.5456 0.6084
0.000 0.3114 0.00712 0.00162 -0.0684 0.5405 0.6098
0.250 0.3401 0.00713 0.00163 -0.0687 0.5364 0.6111
0.500 0.3683 0.00717 0.00165 -0.0689 0.5305 0.6121
0.750 0.3960 0.00722 0.00168 -0.0691 0.5241 0.6132
1.000 0.4244 0.00726 0.00170 -0.0693 0.5194 0.6142
1.250 0.4525 0.00730 0.00174 -0.0695 0.5131 0.6153
1.500 0.4797 0.00738 0.00178 -0.0696 0.5049 0.6164
1.750 0.5072 0.00746 0.00182 -0.0697 0.4932 0.6175
2.000 0.5342 0.00755 0.00187 -0.0697 0.4814 0.6186
2.250 0.5613 0.00764 0.00193 -0.0697 0.4727 0.6197
2.500 0.5888 0.00772 0.00199 -0.0698 0.4650 0.6207
2.750 0.6154 0.00783 0.00207 -0.0698 0.4544 0.6218
3.000 0.6424 0.00793 0.00214 -0.0698 0.4436 0.6229
3.250 0.6688 0.00805 0.00223 -0.0697 0.4322 0.6240
3.500 0.6942 0.00823 0.00234 -0.0695 0.4154 0.6250
3.750 0.7186 0.00845 0.00247 -0.0690 0.3942 0.6259
4.000 0.7413 0.00873 0.00265 -0.0683 0.3677 0.6274
4.250 0.7637 0.00903 0.00285 -0.0675 0.3401 0.6288
4.500 0.7862 0.00931 0.00305 -0.0668 0.3179 0.6301
4.750 0.8084 0.00962 0.00327 -0.0660 0.2947 0.6314
5.000 0.8302 0.00992 0.00350 -0.0651 0.2735 0.6327
5.250 0.8519 0.01022 0.00373 -0.0642 0.2546 0.6341
5.500 0.8728 0.01053 0.00397 -0.0632 0.2349 0.6354
5.750 0.8931 0.01087 0.00423 -0.0621 0.2176 0.6368
6.250 0.9366 0.01134 0.00468 -0.0603 0.2026 0.6395
6.500 0.9578 0.01156 0.00490 -0.0593 0.1976 0.6408
6.750 0.9771 0.01178 0.00512 -0.0579 0.1928 0.6421
7.000 0.9977 0.01195 0.00531 -0.0568 0.1897 0.6432
7.250 1.0180 0.01214 0.00553 -0.0556 0.1852 0.6447
7.500 1.0357 0.01241 0.00581 -0.0540 0.1786 0.6467
7.750 1.0556 0.01264 0.00607 -0.0528 0.1730 0.6486
8.000 1.0651 0.01323 0.00650 -0.0499 0.1365 0.6504
8.250 1.0742 0.01385 0.00703 -0.0470 0.1202 0.6522
8.500 1.0876 0.01431 0.00750 -0.0449 0.1128 0.6540
8.750 1.1028 0.01472 0.00793 -0.0431 0.1070 0.6558
9.000 1.1162 0.01521 0.00843 -0.0411 0.1008 0.6576
9.250 1.1289 0.01575 0.00896 -0.0391 0.0926 0.6593
9.500 1.1399 0.01638 0.00956 -0.0370 0.0827 0.6609
9.750 1.1494 0.01711 0.01024 -0.0347 0.0724 0.6623
10.000 1.1587 0.01787 0.01099 -0.0325 0.0636 0.6645
10.250 1.1671 0.01872 0.01183 -0.0304 0.0549 0.6668
10.500 1.1763 0.01958 0.01269 -0.0284 0.0484 0.6691
10.750 1.1840 0.02056 0.01366 -0.0265 0.0415 0.6714
11.000 1.1920 0.02158 0.01468 -0.0246 0.0355 0.6737
11.250 1.2006 0.02261 0.01572 -0.0230 0.0308 0.6762
11.500 1.2093 0.02368 0.01680 -0.0214 0.0270 0.6786
12.000 1.2272 0.02592 0.01910 -0.0187 0.0215 0.6839
12.250 1.2352 0.02715 0.02037 -0.0175 0.0189 0.6868
12.500 1.2434 0.02841 0.02167 -0.0163 0.0168 0.6899
12.750 1.2502 0.02982 0.02311 -0.0151 0.0144 0.6928
13.000 1.2578 0.03121 0.02455 -0.0141 0.0130 0.6958
13.250 1.2660 0.03260 0.02599 -0.0132 0.0120 0.6985
13.500 1.2726 0.03416 0.02759 -0.0123 0.0106 0.7018
13.750 1.2800 0.03570 0.02920 -0.0116 0.0096 0.7055
14.000 1.2865 0.03735 0.03091 -0.0109 0.0087 0.7094
14.250 1.2932 0.03903 0.03265 -0.0103 0.0078 0.7133
14.500 1.2986 0.04090 0.03456 -0.0097 0.0070 0.7169
14.750 1.3045 0.04276 0.03650 -0.0093 0.0064 0.7213
15.000 1.3097 0.04472 0.03854 -0.0089 0.0056 0.7262
15.250 1.3138 0.04686 0.04074 -0.0086 0.0051 0.7313
15.750 1.3231 0.05119 0.04523 -0.0084 0.0042 0.7429
16.000 1.3253 0.05370 0.04782 -0.0084 0.0037 0.7498
16.250 1.3295 0.05603 0.05025 -0.0085 0.0035 0.7573
16.500 1.3323 0.05859 0.05291 -0.0087 0.0032 0.7661
16.750 1.3350 0.06122 0.05563 -0.0090 0.0030 0.7752
17.000 1.3364 0.06405 0.05857 -0.0094 0.0028 0.7861
17.250 1.3368 0.06705 0.06168 -0.0099 0.0026 0.7984
17.500 1.3369 0.07015 0.06491 -0.0105 0.0023 0.8144
17.750 1.3379 0.07311 0.06803 -0.0111 0.0022 0.8382
18.000 1.3399 0.07622 0.07151 -0.0122 0.0022 0.9543
18.250 1.3380 0.07976 0.07514 -0.0133 0.0020 1.0000
18.500 1.3367 0.08339 0.07885 -0.0144 0.0019 1.0000
18.750 1.3337 0.08736 0.08290 -0.0158 0.0018 1.0000
19.000 1.3304 0.09144 0.08708 -0.0173 0.0018 1.0000
19.250 1.3255 0.09587 0.09159 -0.0191 0.0016 1.0000
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