EPPLER 542 AIRFOIL (e542-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 542 AIRFOIL (e542-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.69 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e542-il-1000000.txt Download as CSV file: xf-e542-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 542 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7030 0.03892 0.03586 -0.0662 0.9932 0.0055
-11.000 -0.6991 0.03694 0.03375 -0.0653 0.9745 0.0056
-10.750 -0.7207 0.02637 0.02213 -0.0628 0.9561 0.0041
-10.500 -0.6834 0.02381 0.01923 -0.0669 0.9476 0.0042
-10.250 -0.6343 0.02222 0.01745 -0.0731 0.9401 0.0047
-10.000 -0.5843 0.02034 0.01531 -0.0790 0.9283 0.0047
-9.750 -0.5395 0.01969 0.01444 -0.0837 0.9054 0.0051
-9.500 -0.5142 0.01835 0.01284 -0.0839 0.8816 0.0055
-9.000 -0.4784 0.01725 0.01149 -0.0814 0.8456 0.0058
-8.750 -0.4613 0.01667 0.01081 -0.0799 0.8319 0.0058
-8.500 -0.4457 0.01600 0.01004 -0.0781 0.8196 0.0058
-8.250 -0.4272 0.01568 0.00964 -0.0769 0.8086 0.0061
-8.000 -0.4107 0.01518 0.00906 -0.0752 0.7977 0.0062
-7.750 -0.3938 0.01472 0.00852 -0.0737 0.7880 0.0063
-7.250 -0.3594 0.01389 0.00756 -0.0706 0.7699 0.0066
-6.750 -0.3226 0.01322 0.00677 -0.0679 0.7541 0.0071
-6.500 -0.3064 0.01281 0.00629 -0.0661 0.7465 0.0075
-6.250 -0.2887 0.01244 0.00590 -0.0646 0.7394 0.0082
-6.000 -0.2703 0.01215 0.00556 -0.0631 0.7323 0.0088
-5.750 -0.2542 0.01177 0.00514 -0.0612 0.7257 0.0109
-5.500 -0.2376 0.01142 0.00477 -0.0594 0.7192 0.0153
-5.250 -0.2251 0.01097 0.00440 -0.0569 0.7130 0.0334
-5.000 -0.2124 0.01054 0.00408 -0.0544 0.7074 0.0586
-4.750 -0.2021 0.01015 0.00380 -0.0515 0.7015 0.0870
-4.500 -0.1956 0.00987 0.00359 -0.0476 0.6956 0.1180
-4.250 -0.1853 0.00947 0.00337 -0.0446 0.6905 0.1632
-4.000 -0.1781 0.00892 0.00310 -0.0411 0.6851 0.2391
-3.750 -0.1841 0.00780 0.00262 -0.0353 0.6800 0.4059
-3.500 -0.1894 0.00623 0.00196 -0.0298 0.6757 0.6300
-3.250 -0.1664 0.00616 0.00216 -0.0288 0.6712 0.7200
-3.000 -0.1383 0.00630 0.00223 -0.0289 0.6667 0.7338
-2.750 -0.1101 0.00649 0.00234 -0.0290 0.6623 0.7440
-2.500 -0.0812 0.00667 0.00252 -0.0292 0.6584 0.7506
-2.250 -0.0523 0.00692 0.00274 -0.0294 0.6544 0.7579
-2.000 -0.0238 0.00721 0.00301 -0.0294 0.6504 0.7642
-1.750 0.0055 0.00771 0.00350 -0.0294 0.6463 0.7709
-1.500 0.0345 0.00807 0.00385 -0.0294 0.6428 0.7776
-1.250 0.0630 0.00818 0.00396 -0.0295 0.6392 0.7796
-1.000 0.0911 0.00818 0.00391 -0.0298 0.6355 0.7804
-0.750 0.1191 0.00820 0.00387 -0.0301 0.6316 0.7812
-0.500 0.1475 0.00819 0.00384 -0.0304 0.6283 0.7819
-0.250 0.1758 0.00815 0.00379 -0.0308 0.6249 0.7826
0.000 0.2041 0.00814 0.00375 -0.0311 0.6213 0.7835
0.250 0.2321 0.00815 0.00371 -0.0314 0.6178 0.7843
0.500 0.2602 0.00816 0.00368 -0.0318 0.6140 0.7850
0.750 0.2885 0.00812 0.00363 -0.0322 0.6107 0.7857
1.000 0.3167 0.00809 0.00359 -0.0325 0.6068 0.7864
1.250 0.3445 0.00808 0.00355 -0.0328 0.6026 0.7872
1.500 0.3723 0.00812 0.00354 -0.0331 0.5980 0.7881
1.750 0.4005 0.00809 0.00352 -0.0335 0.5945 0.7888
2.000 0.4287 0.00806 0.00350 -0.0338 0.5905 0.7894
2.250 0.4564 0.00807 0.00348 -0.0341 0.5862 0.7900
2.500 0.4841 0.00811 0.00348 -0.0344 0.5817 0.7906
2.750 0.5123 0.00808 0.00348 -0.0348 0.5776 0.7911
3.000 0.5401 0.00809 0.00348 -0.0351 0.5730 0.7916
3.250 0.5674 0.00813 0.00349 -0.0353 0.5682 0.7920
3.500 0.5951 0.00815 0.00353 -0.0355 0.5636 0.7925
3.750 0.6223 0.00807 0.00347 -0.0357 0.5584 0.7935
4.000 0.6490 0.00807 0.00347 -0.0358 0.5528 0.7942
4.250 0.6760 0.00808 0.00349 -0.0359 0.5473 0.7947
4.500 0.7031 0.00809 0.00352 -0.0361 0.5411 0.7953
5.000 0.7561 0.00816 0.00362 -0.0361 0.5277 0.7964
5.250 0.7814 0.00823 0.00368 -0.0359 0.5194 0.7970
5.500 0.8078 0.00827 0.00375 -0.0359 0.5100 0.7976
5.750 0.8326 0.00835 0.00383 -0.0356 0.4989 0.7982
6.000 0.8567 0.00846 0.00392 -0.0352 0.4860 0.7988
6.250 0.8799 0.00859 0.00403 -0.0346 0.4689 0.7995
6.500 0.9016 0.00878 0.00416 -0.0337 0.4473 0.8002
6.750 0.9205 0.00905 0.00434 -0.0323 0.4214 0.8009
7.000 0.9369 0.00940 0.00458 -0.0305 0.3907 0.8019
7.250 0.9512 0.00981 0.00486 -0.0283 0.3592 0.8029
7.500 0.9612 0.01024 0.00515 -0.0252 0.3271 0.8039
7.750 0.9695 0.01070 0.00548 -0.0219 0.2956 0.8048
8.000 0.9782 0.01123 0.00587 -0.0187 0.2657 0.8057
8.250 0.9876 0.01177 0.00629 -0.0158 0.2395 0.8065
8.500 0.9958 0.01236 0.00675 -0.0127 0.2123 0.8072
8.750 1.0059 0.01289 0.00721 -0.0101 0.1935 0.8079
9.000 1.0135 0.01353 0.00774 -0.0072 0.1705 0.8084
9.250 1.0215 0.01411 0.00825 -0.0044 0.1522 0.8097
9.500 1.0247 0.01493 0.00895 -0.0011 0.1278 0.8109
9.750 1.0336 0.01559 0.00958 0.0012 0.1147 0.8119
10.000 1.0367 0.01655 0.01042 0.0042 0.0955 0.8129
10.250 1.0426 0.01745 0.01127 0.0067 0.0809 0.8139
10.500 1.0531 0.01820 0.01202 0.0085 0.0739 0.8150
10.750 1.0591 0.01920 0.01298 0.0107 0.0625 0.8162
11.000 1.0661 0.02020 0.01395 0.0126 0.0533 0.8173
11.250 1.0755 0.02113 0.01488 0.0142 0.0470 0.8183
11.500 1.0840 0.02214 0.01589 0.0157 0.0414 0.8193
11.750 1.0905 0.02330 0.01703 0.0174 0.0343 0.8203
12.000 1.0984 0.02443 0.01815 0.0187 0.0298 0.8212
12.250 1.1058 0.02563 0.01935 0.0201 0.0255 0.8221
12.500 1.1136 0.02684 0.02057 0.0213 0.0221 0.8229
12.750 1.1234 0.02796 0.02172 0.0223 0.0204 0.8236
13.000 1.1303 0.02931 0.02309 0.0234 0.0179 0.8242
13.250 1.1389 0.03054 0.02435 0.0243 0.0159 0.8255
13.500 1.1465 0.03188 0.02573 0.0252 0.0145 0.8268
13.750 1.1547 0.03323 0.02713 0.0260 0.0129 0.8279
14.000 1.1615 0.03473 0.02866 0.0267 0.0119 0.8290
14.250 1.1694 0.03617 0.03015 0.0274 0.0102 0.8301
14.500 1.1759 0.03778 0.03182 0.0280 0.0093 0.8312
14.750 1.1835 0.03935 0.03344 0.0285 0.0082 0.8323
15.000 1.1885 0.04117 0.03529 0.0289 0.0064 0.8335
15.250 1.1934 0.04306 0.03723 0.0293 0.0056 0.8348
15.500 1.1859 0.04617 0.04037 0.0301 0.0023 0.8359
15.750 1.1907 0.04823 0.04249 0.0302 0.0022 0.8370
16.000 1.1916 0.05072 0.04506 0.0304 0.0019 0.8379
16.250 1.1940 0.05313 0.04755 0.0303 0.0018 0.8388
16.500 1.1953 0.05575 0.05026 0.0302 0.0016 0.8396
16.750 1.1971 0.05836 0.05296 0.0299 0.0014 0.8407
17.000 1.1976 0.06118 0.05589 0.0295 0.0014 0.8421
17.250 1.1984 0.06404 0.05884 0.0290 0.0013 0.8434
17.500 1.1984 0.06707 0.06196 0.0284 0.0013 0.8447
17.750 1.1898 0.07131 0.06634 0.0274 0.0011 0.8458
18.000 1.1922 0.07421 0.06932 0.0265 0.0011 0.8470
18.250 1.1896 0.07787 0.07308 0.0253 0.0011 0.8481
18.500 1.1874 0.08158 0.07689 0.0240 0.0011 0.8493
18.750 1.1738 0.08709 0.08255 0.0220 0.0010 0.8502
19.000 1.1671 0.09174 0.08732 0.0201 0.0010 0.8512
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