EPPLER 545 AIRFOIL (e545-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 545 AIRFOIL (e545-il) Reynolds number: 100,000 Max Cl/Cd: 43.29 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e545-il-100000.txt Download as CSV file: xf-e545-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3933 0.10861 0.10387 -0.0511 1.0000 0.1444
-11.000 -0.4363 0.07704 0.07267 -0.0687 1.0000 0.0735
-10.750 -0.4876 0.06899 0.06451 -0.0694 1.0000 0.0639
-10.500 -0.5284 0.06544 0.06093 -0.0668 1.0000 0.0627
-10.250 -0.5617 0.06395 0.05946 -0.0626 1.0000 0.0627
-10.000 -0.5910 0.06321 0.05876 -0.0579 1.0000 0.0635
-9.750 -0.6227 0.06284 0.05842 -0.0531 1.0000 0.0646
-9.000 -0.7870 0.06092 0.05513 -0.0374 0.9950 0.0532
-8.750 -0.7694 0.05483 0.04860 -0.0388 0.9883 0.0466
-8.500 -0.7541 0.04919 0.04207 -0.0397 0.9808 0.0419
-8.250 -0.7308 0.04585 0.03842 -0.0407 0.9729 0.0413
-8.000 -0.7076 0.04269 0.03448 -0.0415 0.9654 0.0422
-7.750 -0.6748 0.04033 0.03221 -0.0435 0.9590 0.0445
-7.500 -0.6356 0.03764 0.02911 -0.0458 0.9547 0.0458
-7.250 -0.6054 0.03561 0.02678 -0.0459 0.9473 0.0466
-7.000 -0.5619 0.03349 0.02459 -0.0480 0.9431 0.0494
-6.750 -0.5158 0.03184 0.02299 -0.0511 0.9398 0.0563
-6.500 -0.4902 0.03067 0.02192 -0.0507 0.9315 0.0638
-6.250 -0.4588 0.02919 0.02063 -0.0516 0.9257 0.0792
-6.000 -0.4434 0.02789 0.01957 -0.0503 0.9171 0.1030
-5.750 -0.4379 0.02565 0.01804 -0.0483 0.9080 0.1745
-5.500 -0.4603 0.02276 0.01677 -0.0429 0.8953 0.3923
-5.250 -0.4193 0.02831 0.02293 -0.0367 0.8900 0.6292
-5.000 -0.3554 0.03297 0.02736 -0.0350 0.8884 0.6637
-4.750 -0.2344 0.03815 0.03217 -0.0396 0.8921 0.6892
-4.500 -0.0839 0.03971 0.03324 -0.0546 0.9019 0.7234
-4.250 -0.0266 0.03957 0.03291 -0.0585 0.8971 0.7431
-4.000 0.0307 0.03896 0.03210 -0.0633 0.8933 0.7613
-3.750 0.0909 0.03815 0.03112 -0.0689 0.8904 0.7805
-3.500 0.1456 0.03752 0.03033 -0.0737 0.8873 0.8046
-3.250 0.1355 0.03766 0.03042 -0.0688 0.8737 0.8069
-2.750 0.3708 0.03291 0.02537 -0.0975 0.8745 0.9404
-2.500 0.4195 0.03160 0.02394 -0.1030 0.8691 0.9545
-1.750 0.2873 0.03470 0.02697 -0.0720 0.8302 0.8416
-1.500 0.2967 0.03447 0.02672 -0.0701 0.8206 0.8396
-1.250 0.3160 0.03402 0.02621 -0.0697 0.8149 0.8397
-1.000 0.3127 0.03418 0.02638 -0.0656 0.8053 0.8378
-0.750 0.3240 0.03393 0.02609 -0.0638 0.7986 0.8376
-0.500 0.3369 0.03370 0.02582 -0.0622 0.7933 0.8379
-0.250 0.3103 0.03429 0.02645 -0.0542 0.7823 0.8357
0.000 0.3287 0.03385 0.02596 -0.0533 0.7777 0.8369
0.250 0.2298 0.03526 0.02746 -0.0332 0.7632 0.8342
0.500 0.2497 0.03477 0.02692 -0.0326 0.7594 0.8360
0.750 0.1208 0.03598 0.02821 -0.0090 0.7431 0.8368
1.000 0.1634 0.03542 0.02758 -0.0121 0.7407 0.8386
1.250 0.0816 0.03667 0.02887 0.0018 0.7263 0.8408
1.500 0.1235 0.03614 0.02828 -0.0009 0.7232 0.8421
1.750 0.1063 0.03708 0.02925 0.0040 0.7134 0.8446
2.000 0.1300 0.03706 0.02921 0.0038 0.7076 0.8461
2.250 0.1802 0.03631 0.02843 0.0004 0.7045 0.8471
2.500 0.2280 0.03566 0.02776 -0.0026 0.7013 0.8482
2.750 0.1986 0.03726 0.02939 0.0030 0.6884 0.8511
3.000 0.2518 0.03634 0.02845 -0.0004 0.6857 0.8528
3.250 0.2333 0.03802 0.03016 0.0033 0.6734 0.8558
3.500 0.2782 0.03741 0.02956 0.0007 0.6693 0.8572
3.750 0.3375 0.03611 0.02826 -0.0032 0.6671 0.8584
4.000 0.4033 0.03467 0.02683 -0.0079 0.6656 0.8595
4.250 0.3700 0.03677 0.02899 -0.0017 0.6503 0.8624
4.500 0.3619 0.03835 0.03061 0.0012 0.6380 0.8657
4.750 0.4037 0.03762 0.02995 -0.0004 0.6339 0.8683
5.000 0.4592 0.03613 0.02852 -0.0031 0.6318 0.8705
5.250 0.5259 0.03433 0.02679 -0.0075 0.6306 0.8722
5.500 0.5049 0.03654 0.02905 -0.0035 0.6152 0.8758
5.750 0.5003 0.03817 0.03076 -0.0011 0.6030 0.8791
6.000 0.5399 0.03730 0.02997 -0.0020 0.5987 0.8817
6.250 0.5947 0.03563 0.02842 -0.0044 0.5969 0.8842
6.500 0.6254 0.03539 0.02827 -0.0049 0.5905 0.8879
6.750 0.6431 0.03574 0.02873 -0.0044 0.5805 0.8923
7.000 0.7149 0.03308 0.02620 -0.0082 0.5788 0.8948
7.250 0.8088 0.03008 0.02333 -0.0156 0.5762 0.8967
7.500 0.7945 0.03099 0.02436 -0.0103 0.5621 0.9027
7.750 0.8230 0.03053 0.02402 -0.0103 0.5521 0.9074
8.000 0.8806 0.02898 0.02261 -0.0137 0.5439 0.9107
8.250 0.8939 0.02881 0.02258 -0.0114 0.5315 0.9169
8.500 0.9504 0.02726 0.02111 -0.0147 0.5202 0.9214
8.750 0.9910 0.02615 0.02007 -0.0159 0.5062 0.9271
9.000 1.0074 0.02574 0.01979 -0.0139 0.4899 0.9362
9.250 1.0294 0.02519 0.01932 -0.0127 0.4722 0.9458
9.500 1.0469 0.02496 0.01920 -0.0113 0.4522 0.9583
9.750 1.0667 0.02512 0.01949 -0.0111 0.4288 0.9758
10.000 1.0880 0.02513 0.01948 -0.0111 0.4059 1.0000
10.250 1.1006 0.02564 0.01996 -0.0102 0.3833 1.0000
10.500 1.1105 0.02645 0.02075 -0.0092 0.3598 1.0000
10.750 1.1226 0.02734 0.02148 -0.0086 0.3358 1.0000
11.000 1.1264 0.02873 0.02285 -0.0073 0.3118 1.0000
11.250 1.1311 0.03018 0.02414 -0.0062 0.2876 1.0000
11.500 1.1299 0.03206 0.02595 -0.0048 0.2632 1.0000
11.750 1.1281 0.03406 0.02779 -0.0033 0.2394 1.0000
12.000 1.1250 0.03629 0.02988 -0.0020 0.2164 1.0000
12.250 1.1234 0.03856 0.03198 -0.0008 0.1950 1.0000
12.500 1.1221 0.04089 0.03417 0.0003 0.1756 1.0000
12.750 1.1170 0.04349 0.03686 0.0011 0.1588 1.0000
13.000 1.1134 0.04609 0.03941 0.0018 0.1444 1.0000
13.250 1.1126 0.04861 0.04176 0.0024 0.1315 1.0000
13.500 1.1189 0.05082 0.04375 0.0032 0.1176 1.0000
13.750 1.1303 0.05287 0.04566 0.0039 0.1047 1.0000
14.000 1.1375 0.05521 0.04803 0.0043 0.0948 1.0000
14.250 1.1434 0.05763 0.05051 0.0047 0.0867 1.0000
14.500 1.1518 0.05990 0.05277 0.0050 0.0795 1.0000
14.750 1.1618 0.06203 0.05481 0.0051 0.0728 1.0000
15.000 1.1616 0.06501 0.05800 0.0052 0.0680 1.0000
15.250 1.1682 0.06767 0.06072 0.0053 0.0629 1.0000
15.500 1.1809 0.06989 0.06287 0.0054 0.0579 1.0000
15.750 1.1736 0.07371 0.06702 0.0052 0.0551 1.0000
16.000 1.1833 0.07630 0.06957 0.0050 0.0512 1.0000
16.250 1.1717 0.08085 0.07449 0.0044 0.0494 1.0000
16.500 1.1850 0.08302 0.07653 0.0042 0.0458 1.0000
16.750 1.1666 0.08836 0.08224 0.0029 0.0450 1.0000
17.000 1.1484 0.09402 0.08824 0.0011 0.0441 1.0000
17.250 1.1327 0.09960 0.09408 -0.0009 0.0432 1.0000
17.500 1.1502 0.10139 0.09573 -0.0009 0.0405 1.0000
17.750 1.1291 0.10786 0.10251 -0.0038 0.0404 1.0000
18.000 1.1086 0.11464 0.10954 -0.0070 0.0404 1.0000
18.250 1.0855 0.12211 0.11725 -0.0111 0.0404 1.0000
18.500 1.0645 0.12974 0.12508 -0.0155 0.0405 1.0000
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