EPPLER 547 AIRFOIL (e547-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 547 AIRFOIL (e547-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.9 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e547-il-1000000-n5.txt Download as CSV file: xf-e547-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 547 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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7097 0.09968 0.09746 -0.0470 1.0000 0.0026
-16.250 -0.7599 0.08382 0.08135 -0.0559 1.0000 0.0026
-16.000 -0.7919 0.07348 0.07079 -0.0619 1.0000 0.0026
-15.750 -0.8060 0.06738 0.06458 -0.0650 1.0000 0.0026
-15.500 -0.8220 0.06161 0.05866 -0.0676 1.0000 0.0026
-15.250 -0.8337 0.05695 0.05387 -0.0691 1.0000 0.0026
-15.000 -0.8479 0.05242 0.04917 -0.0699 1.0000 0.0026
-14.750 -0.8591 0.04857 0.04516 -0.0701 1.0000 0.0026
-14.500 -0.8708 0.04496 0.04138 -0.0698 1.0000 0.0026
-14.250 -0.8737 0.04247 0.03878 -0.0692 1.0000 0.0026
-14.000 -0.8795 0.03981 0.03598 -0.0681 1.0000 0.0026
-13.750 -0.8797 0.03778 0.03383 -0.0671 1.0000 0.0026
-13.500 -0.8794 0.03585 0.03180 -0.0658 1.0000 0.0026
-13.250 -0.8794 0.03395 0.02978 -0.0642 1.0000 0.0026
-13.000 -0.8774 0.03228 0.02799 -0.0626 1.0000 0.0026
-12.750 -0.8701 0.03065 0.02625 -0.0618 0.9996 0.0026
-12.500 -0.8572 0.02885 0.02433 -0.0619 0.9921 0.0026
-12.250 -0.8387 0.02730 0.02265 -0.0628 0.9646 0.0026
-12.000 -0.7917 0.02559 0.02080 -0.0695 0.9486 0.0026
-11.750 -0.7376 0.02384 0.01888 -0.0777 0.9366 0.0026
-11.500 -0.6814 0.02223 0.01703 -0.0861 0.9083 0.0027
-11.250 -0.6581 0.02154 0.01613 -0.0868 0.8727 0.0027
-11.000 -0.6461 0.02081 0.01524 -0.0852 0.8481 0.0027
-10.750 -0.6344 0.02008 0.01437 -0.0835 0.8294 0.0027
-10.500 -0.6203 0.01950 0.01369 -0.0821 0.8138 0.0027
-10.250 -0.6106 0.01863 0.01268 -0.0800 0.7992 0.0028
-9.750 -0.5854 0.01724 0.01110 -0.0765 0.7745 0.0030
-9.500 -0.5685 0.01682 0.01060 -0.0753 0.7642 0.0029
-9.250 -0.5529 0.01634 0.01004 -0.0739 0.7541 0.0029
-9.000 -0.5387 0.01575 0.00939 -0.0722 0.7443 0.0031
-8.750 -0.5228 0.01529 0.00887 -0.0708 0.7353 0.0033
-8.500 -0.5071 0.01484 0.00836 -0.0693 0.7262 0.0034
-8.250 -0.4906 0.01443 0.00790 -0.0678 0.7176 0.0034
-8.000 -0.4751 0.01402 0.00742 -0.0662 0.7092 0.0037
-7.750 -0.4592 0.01362 0.00698 -0.0645 0.7018 0.0039
-7.500 -0.4442 0.01327 0.00656 -0.0627 0.6937 0.0040
-7.250 -0.4296 0.01294 0.00619 -0.0607 0.6857 0.0041
-7.000 -0.4164 0.01269 0.00588 -0.0583 0.6784 0.0044
-6.750 -0.4002 0.01241 0.00557 -0.0564 0.6717 0.0047
-6.500 -0.3815 0.01215 0.00528 -0.0551 0.6648 0.0056
-6.250 -0.3613 0.01193 0.00501 -0.0539 0.6586 0.0063
-6.000 -0.3409 0.01168 0.00474 -0.0528 0.6516 0.0075
-5.750 -0.3200 0.01146 0.00449 -0.0518 0.6447 0.0095
-5.500 -0.2979 0.01124 0.00426 -0.0510 0.6382 0.0119
-5.250 -0.2761 0.01102 0.00403 -0.0502 0.6319 0.0168
-5.000 -0.2536 0.01078 0.00382 -0.0494 0.6265 0.0239
-4.750 -0.2311 0.01055 0.00360 -0.0487 0.6202 0.0340
-4.500 -0.2097 0.01026 0.00338 -0.0478 0.6140 0.0551
-4.250 -0.1884 0.00989 0.00315 -0.0470 0.6084 0.0894
-4.000 -0.1681 0.00947 0.00291 -0.0460 0.6022 0.1394
-3.750 -0.1487 0.00892 0.00263 -0.0450 0.5973 0.2144
-3.500 -0.1310 0.00814 0.00227 -0.0438 0.5921 0.3270
-3.250 -0.1131 0.00729 0.00186 -0.0426 0.5865 0.4559
-3.000 -0.0926 0.00662 0.00163 -0.0418 0.5815 0.5812
-2.750 -0.0651 0.00658 0.00165 -0.0418 0.5758 0.6166
-2.500 -0.0369 0.00663 0.00167 -0.0420 0.5705 0.6341
-2.250 -0.0085 0.00669 0.00171 -0.0422 0.5660 0.6455
-2.000 0.0201 0.00677 0.00176 -0.0424 0.5610 0.6562
-1.750 0.0485 0.00687 0.00183 -0.0425 0.5555 0.6633
-1.500 0.0772 0.00691 0.00180 -0.0429 0.5508 0.6651
-1.250 0.1060 0.00693 0.00177 -0.0432 0.5461 0.6661
-1.000 0.1346 0.00696 0.00175 -0.0435 0.5414 0.6669
-0.750 0.1631 0.00700 0.00173 -0.0438 0.5369 0.6676
-0.500 0.1918 0.00700 0.00171 -0.0441 0.5323 0.6685
-0.250 0.2203 0.00702 0.00171 -0.0444 0.5275 0.6695
0.000 0.2484 0.00706 0.00171 -0.0446 0.5231 0.6705
0.250 0.2771 0.00708 0.00173 -0.0449 0.5191 0.6715
0.500 0.3056 0.00711 0.00174 -0.0452 0.5144 0.6724
0.750 0.3338 0.00716 0.00176 -0.0455 0.5100 0.6733
1.000 0.3621 0.00721 0.00178 -0.0457 0.5060 0.6742
1.250 0.3907 0.00724 0.00181 -0.0461 0.5018 0.6751
1.500 0.4189 0.00729 0.00184 -0.0463 0.4974 0.6760
1.750 0.4467 0.00736 0.00188 -0.0465 0.4929 0.6769
2.000 0.4751 0.00740 0.00191 -0.0468 0.4889 0.6778
2.250 0.5033 0.00745 0.00196 -0.0471 0.4843 0.6787
2.500 0.5311 0.00752 0.00201 -0.0473 0.4794 0.6797
2.750 0.5589 0.00759 0.00206 -0.0475 0.4747 0.6807
3.000 0.5869 0.00765 0.00212 -0.0477 0.4693 0.6817
3.250 0.6142 0.00774 0.00218 -0.0478 0.4634 0.6825
3.500 0.6419 0.00780 0.00225 -0.0480 0.4579 0.6833
3.750 0.6693 0.00787 0.00232 -0.0481 0.4515 0.6843
4.000 0.6961 0.00796 0.00241 -0.0481 0.4457 0.6853
4.250 0.7236 0.00802 0.00249 -0.0483 0.4398 0.6863
4.500 0.7502 0.00813 0.00259 -0.0483 0.4330 0.6873
4.750 0.7772 0.00821 0.00269 -0.0484 0.4268 0.6884
5.000 0.8036 0.00832 0.00279 -0.0483 0.4192 0.6894
5.250 0.8299 0.00843 0.00291 -0.0483 0.4111 0.6905
5.500 0.8553 0.00859 0.00304 -0.0481 0.4010 0.6916
5.750 0.8807 0.00873 0.00317 -0.0479 0.3892 0.6927
6.000 0.9057 0.00890 0.00333 -0.0476 0.3774 0.6938
6.250 0.9293 0.00912 0.00350 -0.0471 0.3617 0.6951
6.500 0.9521 0.00938 0.00370 -0.0465 0.3447 0.6963
6.750 0.9734 0.00969 0.00394 -0.0455 0.3248 0.6974
7.000 0.9933 0.01005 0.00421 -0.0444 0.3018 0.6984
7.250 1.0115 0.01045 0.00452 -0.0430 0.2785 0.6997
7.500 1.0283 0.01088 0.00486 -0.0413 0.2547 0.7010
7.750 1.0439 0.01131 0.00521 -0.0394 0.2327 0.7023
8.000 1.0558 0.01174 0.00556 -0.0368 0.2116 0.7037
8.250 1.0671 0.01222 0.00596 -0.0342 0.1922 0.7051
8.500 1.0796 0.01269 0.00637 -0.0318 0.1755 0.7066
8.750 1.0892 0.01327 0.00687 -0.0290 0.1555 0.7081
9.000 1.0987 0.01387 0.00740 -0.0263 0.1389 0.7096
9.250 1.1091 0.01445 0.00793 -0.0239 0.1251 0.7111
9.500 1.1195 0.01506 0.00850 -0.0216 0.1133 0.7126
9.750 1.1288 0.01573 0.00914 -0.0192 0.1015 0.7141
10.000 1.1391 0.01638 0.00979 -0.0171 0.0928 0.7159
10.250 1.1478 0.01715 0.01054 -0.0149 0.0840 0.7178
10.500 1.1550 0.01802 0.01141 -0.0127 0.0744 0.7198
10.750 1.1633 0.01891 0.01229 -0.0107 0.0663 0.7217
11.000 1.1695 0.01996 0.01332 -0.0087 0.0576 0.7236
11.250 1.1773 0.02098 0.01435 -0.0069 0.0524 0.7256
11.500 1.1821 0.02224 0.01558 -0.0051 0.0441 0.7274
11.750 1.1829 0.02380 0.01709 -0.0030 0.0343 0.7292
12.000 1.1911 0.02497 0.01830 -0.0018 0.0308 0.7312
12.250 1.1963 0.02638 0.01973 -0.0004 0.0267 0.7334
12.500 1.2063 0.02752 0.02093 0.0006 0.0259 0.7357
12.750 1.2084 0.02925 0.02266 0.0019 0.0206 0.7381
13.000 1.2150 0.03072 0.02417 0.0029 0.0186 0.7406
13.250 1.2202 0.03234 0.02582 0.0038 0.0165 0.7430
13.500 1.2275 0.03386 0.02739 0.0045 0.0154 0.7452
13.750 1.2324 0.03561 0.02918 0.0052 0.0138 0.7481
14.000 1.2368 0.03744 0.03108 0.0058 0.0119 0.7513
14.250 1.2430 0.03919 0.03289 0.0063 0.0113 0.7545
14.500 1.2469 0.04121 0.03495 0.0067 0.0102 0.7577
14.750 1.2527 0.04310 0.03690 0.0070 0.0094 0.7608
15.000 1.2575 0.04511 0.03898 0.0072 0.0086 0.7642
15.250 1.2604 0.04737 0.04130 0.0074 0.0076 0.7680
15.500 1.2647 0.04955 0.04355 0.0074 0.0068 0.7719
15.750 1.2686 0.05185 0.04591 0.0074 0.0063 0.7757
16.000 1.2718 0.05422 0.04835 0.0072 0.0058 0.7799
16.250 1.2750 0.05667 0.05089 0.0070 0.0054 0.7848
16.500 1.2761 0.05942 0.05371 0.0067 0.0045 0.7898
16.750 1.2793 0.06196 0.05634 0.0063 0.0044 0.7951
17.000 1.2804 0.06479 0.05925 0.0058 0.0038 0.8015
17.500 1.2835 0.07055 0.06520 0.0045 0.0034 0.8164
17.750 1.2828 0.07377 0.06852 0.0037 0.0029 0.8255
18.000 1.2817 0.07710 0.07196 0.0028 0.0027 0.8373
18.250 1.2807 0.08038 0.07538 0.0020 0.0024 0.8545
18.500 1.2786 0.08321 0.07850 0.0019 0.0024 0.9179
18.750 1.2844 0.08733 0.08277 -0.0016 0.0022 1.0000
19.000 1.2820 0.09115 0.08668 -0.0030 0.0020 1.0000
19.250 1.2789 0.09511 0.09072 -0.0045 0.0019 1.0000
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Polar data table (+)
Polar graphs
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