EPPLER 546 AIRFOIL (e546-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 546 AIRFOIL (e546-il) Reynolds number: 500,000 Max Cl/Cd: 82.63 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e546-il-500000-n5.txt Download as CSV file: xf-e546-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 546 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.4709 0.13540 0.13293 -0.0317 1.0000 0.0046
-14.000 -0.6385 0.07933 0.07671 -0.0563 1.0000 0.0040
-13.750 -0.6816 0.06729 0.06440 -0.0633 1.0000 0.0040
-13.500 -0.6959 0.06223 0.05920 -0.0654 1.0000 0.0041
-13.250 -0.7410 0.05381 0.05043 -0.0669 1.0000 0.0039
-13.000 -0.7501 0.05062 0.04711 -0.0668 1.0000 0.0040
-12.750 -0.7662 0.04675 0.04303 -0.0659 1.0000 0.0040
-12.500 -0.7773 0.04365 0.03974 -0.0647 1.0000 0.0040
-12.250 -0.7887 0.04057 0.03643 -0.0628 1.0000 0.0040
-12.000 -0.7994 0.03756 0.03317 -0.0606 1.0000 0.0040
-11.750 -0.7985 0.03598 0.03147 -0.0587 1.0000 0.0041
-11.500 -0.8015 0.03388 0.02918 -0.0563 1.0000 0.0041
-11.250 -0.8013 0.03218 0.02731 -0.0538 1.0000 0.0042
-11.000 -0.7998 0.03069 0.02567 -0.0513 1.0000 0.0042
-10.500 -0.7595 0.02753 0.02216 -0.0527 0.9930 0.0045
-10.000 -0.7199 0.02485 0.01916 -0.0528 0.9686 0.0047
-9.500 -0.6557 0.02244 0.01646 -0.0573 0.9477 0.0050
-9.250 -0.6156 0.02097 0.01489 -0.0613 0.9394 0.0052
-9.000 -0.5700 0.01974 0.01355 -0.0664 0.9289 0.0053
-8.750 -0.5259 0.01867 0.01237 -0.0712 0.9138 0.0055
-8.500 -0.4906 0.01782 0.01138 -0.0740 0.8930 0.0057
-8.250 -0.4673 0.01718 0.01061 -0.0741 0.8707 0.0060
-8.000 -0.4501 0.01659 0.00990 -0.0729 0.8519 0.0062
-7.750 -0.4345 0.01609 0.00927 -0.0714 0.8350 0.0064
-7.500 -0.4200 0.01559 0.00866 -0.0695 0.8202 0.0068
-7.250 -0.4060 0.01513 0.00810 -0.0676 0.8069 0.0069
-7.000 -0.3939 0.01465 0.00755 -0.0652 0.7940 0.0075
-6.750 -0.3817 0.01431 0.00711 -0.0628 0.7822 0.0081
-6.500 -0.3670 0.01399 0.00672 -0.0607 0.7713 0.0086
-6.250 -0.3506 0.01364 0.00631 -0.0589 0.7611 0.0100
-6.000 -0.3323 0.01335 0.00595 -0.0575 0.7512 0.0117
-5.750 -0.3141 0.01301 0.00558 -0.0560 0.7422 0.0155
-5.500 -0.2957 0.01267 0.00524 -0.0546 0.7332 0.0232
-5.250 -0.2764 0.01233 0.00492 -0.0534 0.7244 0.0351
-5.000 -0.2569 0.01200 0.00462 -0.0522 0.7159 0.0527
-4.750 -0.2380 0.01157 0.00431 -0.0510 0.7074 0.0842
-4.500 -0.2207 0.01104 0.00397 -0.0496 0.6998 0.1378
-4.250 -0.2044 0.01033 0.00359 -0.0482 0.6918 0.2200
-4.000 -0.1901 0.00942 0.00310 -0.0465 0.6840 0.3389
-3.750 -0.1801 0.00798 0.00253 -0.0443 0.6764 0.5482
-3.500 -0.1548 0.00797 0.00264 -0.0438 0.6692 0.6163
-3.250 -0.1271 0.00805 0.00269 -0.0438 0.6622 0.6354
-3.000 -0.0995 0.00818 0.00274 -0.0437 0.6547 0.6506
-2.750 -0.0718 0.00836 0.00286 -0.0436 0.6477 0.6643
-2.500 -0.0441 0.00858 0.00302 -0.0435 0.6405 0.6753
-2.250 -0.0164 0.00870 0.00309 -0.0434 0.6342 0.6811
-2.000 0.0117 0.00872 0.00305 -0.0436 0.6271 0.6829
-1.500 0.0678 0.00873 0.00292 -0.0439 0.6140 0.6853
-1.250 0.0959 0.00874 0.00286 -0.0441 0.6075 0.6863
-1.000 0.1239 0.00875 0.00280 -0.0443 0.6014 0.6875
-0.750 0.1520 0.00876 0.00276 -0.0445 0.5947 0.6888
-0.500 0.1798 0.00879 0.00271 -0.0447 0.5887 0.6900
-0.250 0.2081 0.00880 0.00268 -0.0449 0.5829 0.6911
0.000 0.2361 0.00883 0.00265 -0.0451 0.5764 0.6921
0.250 0.2640 0.00886 0.00262 -0.0453 0.5708 0.6930
0.500 0.2922 0.00887 0.00261 -0.0456 0.5649 0.6938
0.750 0.3198 0.00890 0.00261 -0.0457 0.5590 0.6947
1.000 0.3476 0.00894 0.00263 -0.0458 0.5535 0.6957
1.250 0.3755 0.00897 0.00266 -0.0460 0.5477 0.6968
1.500 0.4029 0.00903 0.00269 -0.0461 0.5420 0.6977
1.750 0.4307 0.00908 0.00273 -0.0463 0.5365 0.6987
2.000 0.4584 0.00912 0.00277 -0.0464 0.5307 0.6997
2.500 0.5134 0.00924 0.00288 -0.0467 0.5188 0.7017
2.750 0.5405 0.00931 0.00293 -0.0467 0.5120 0.7028
3.000 0.5677 0.00939 0.00300 -0.0468 0.5052 0.7039
3.250 0.5948 0.00946 0.00307 -0.0468 0.4979 0.7050
3.500 0.6216 0.00955 0.00315 -0.0468 0.4914 0.7062
3.750 0.6488 0.00962 0.00324 -0.0469 0.4842 0.7074
4.000 0.6750 0.00974 0.00333 -0.0468 0.4771 0.7086
4.250 0.7021 0.00981 0.00342 -0.0469 0.4694 0.7097
4.500 0.7277 0.00992 0.00354 -0.0467 0.4611 0.7108
4.750 0.7541 0.01001 0.00366 -0.0466 0.4521 0.7118
5.000 0.7796 0.01013 0.00379 -0.0463 0.4429 0.7129
5.250 0.8051 0.01026 0.00394 -0.0461 0.4329 0.7140
5.500 0.8305 0.01039 0.00409 -0.0459 0.4227 0.7152
5.750 0.8550 0.01055 0.00425 -0.0455 0.4111 0.7164
6.000 0.8789 0.01073 0.00443 -0.0450 0.3976 0.7177
6.250 0.9023 0.01094 0.00462 -0.0444 0.3819 0.7190
6.500 0.9246 0.01119 0.00484 -0.0436 0.3629 0.7204
6.750 0.9452 0.01151 0.00510 -0.0426 0.3402 0.7218
7.000 0.9642 0.01191 0.00540 -0.0413 0.3137 0.7234
7.250 0.9819 0.01235 0.00575 -0.0398 0.2877 0.7249
7.500 0.9978 0.01285 0.00614 -0.0380 0.2608 0.7264
7.750 1.0126 0.01334 0.00657 -0.0360 0.2354 0.7279
8.000 1.0248 0.01384 0.00699 -0.0336 0.2124 0.7294
8.250 1.0356 0.01439 0.00746 -0.0309 0.1893 0.7311
8.500 1.0460 0.01502 0.00799 -0.0283 0.1663 0.7328
8.750 1.0559 0.01568 0.00858 -0.0256 0.1456 0.7346
9.000 1.0671 0.01630 0.00916 -0.0233 0.1303 0.7364
9.250 1.0777 0.01696 0.00978 -0.0210 0.1163 0.7383
9.500 1.0880 0.01765 0.01044 -0.0188 0.1034 0.7402
9.750 1.0977 0.01839 0.01115 -0.0166 0.0915 0.7420
10.000 1.1073 0.01914 0.01192 -0.0144 0.0816 0.7439
10.250 1.1162 0.01996 0.01276 -0.0124 0.0726 0.7459
10.500 1.1241 0.02089 0.01370 -0.0103 0.0641 0.7482
10.750 1.1312 0.02192 0.01473 -0.0083 0.0564 0.7507
11.000 1.1387 0.02298 0.01581 -0.0066 0.0493 0.7534
11.250 1.1461 0.02411 0.01697 -0.0050 0.0435 0.7560
11.500 1.1524 0.02537 0.01824 -0.0034 0.0380 0.7583
11.750 1.1578 0.02673 0.01963 -0.0018 0.0329 0.7608
12.000 1.1636 0.02812 0.02106 -0.0005 0.0284 0.7635
12.250 1.1698 0.02955 0.02254 0.0007 0.0251 0.7664
12.500 1.1744 0.03116 0.02418 0.0018 0.0214 0.7694
12.750 1.1794 0.03282 0.02588 0.0028 0.0189 0.7724
13.000 1.1857 0.03440 0.02755 0.0036 0.0174 0.7755
13.250 1.1891 0.03626 0.02947 0.0044 0.0148 0.7789
13.500 1.1936 0.03810 0.03138 0.0050 0.0131 0.7826
13.750 1.1974 0.04008 0.03342 0.0055 0.0113 0.7866
14.000 1.2014 0.04211 0.03552 0.0059 0.0102 0.7905
14.250 1.2052 0.04419 0.03770 0.0062 0.0092 0.7950
14.500 1.2092 0.04633 0.03995 0.0064 0.0085 0.8002
15.000 1.2147 0.05106 0.04488 0.0065 0.0068 0.8118
15.250 1.2170 0.05356 0.04749 0.0063 0.0061 0.8187
15.500 1.2178 0.05628 0.05031 0.0061 0.0053 0.8264
15.750 1.2195 0.05897 0.05312 0.0058 0.0049 0.8357
16.000 1.2192 0.06194 0.05622 0.0054 0.0044 0.8467
16.250 1.2183 0.06495 0.05937 0.0050 0.0040 0.8621
16.500 1.2166 0.06805 0.06266 0.0046 0.0036 0.8902
16.750 1.2202 0.07156 0.06640 0.0023 0.0034 1.0000
17.000 1.2190 0.07511 0.07005 0.0012 0.0032 1.0000
17.250 1.2150 0.07912 0.07414 -0.0002 0.0029 1.0000
17.500 1.2118 0.08312 0.07824 -0.0016 0.0028 1.0000
17.750 1.2086 0.08722 0.08246 -0.0032 0.0025 1.0000
18.000 1.2047 0.09152 0.08686 -0.0049 0.0025 1.0000
18.250 1.2006 0.09591 0.09136 -0.0068 0.0024 1.0000
18.500 1.1947 0.10070 0.09626 -0.0090 0.0022 1.0000
18.750 1.1896 0.10543 0.10111 -0.0112 0.0022 1.0000
19.000 1.1820 0.11069 0.10649 -0.0137 0.0021 1.0000
19.250 1.1741 0.11608 0.11198 -0.0164 0.0020 1.0000
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Polar data table (+)
Polar graphs
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